A rail control planning generation method, system, electronic device and storage medium

Abstract

The application relates to the technical field of spacecraft orbit control, and specifically discloses an orbit control planning generation method, system, electronic device and storage medium, which comprises the following steps: constructing an orbit control instruction set containing all preset orbit control instructions of a target spacecraft during in-orbit flight, and determining a target orbit control strategy of a target sub-time period after a preset time of the target spacecraft; according to a starting route, a spacecraft state and an orbit control mode of the target spacecraft at the preset time, determining each preset orbit control instruction selected from the orbit control instruction set as a first orbit control instruction to be executed in a target period after the preset time; and correcting instruction basic parameters of each first orbit control instruction based on the target orbit control strategy, a target starting time and an orbit control name, and generating a target orbit control R sequence. The application can reduce the time consumption of orbit control preparation processes such as plan arrangement, countersigning and data generation, improve the efficiency of orbit control planning, and can be used as a backup means for emergency collision avoidance.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spacecraft orbit control technology, and in particular to an orbit control planning generation method and system, an electronic device and a storage medium. BACKGROUND

[0002] In recent years, with the development of microsatellite constellations, the number of near-Earth space targets has increased rapidly. For example, large spacecraft in near-Earth space, with a statistical area of 0.1m 2 The number of space targets above and within an altitude range of 160km-450km at perigee reaches several thousand, including satellites, rocket bodies, space debris, etc. If there is a risk of collision with the target, the spacecraft needs to actively perform orbit maneuver control to avoid collision.

[0003] Large spacecraft orbit maneuver is implemented by spacecraft development departments and flight control centers in coordination. Generally, target warning information is obtained before the spacecraft meets the dangerous target, and orbit control strategy design is performed. In the existing technical solution, the process of implementing one orbit maneuver control includes flight program scheduling, instruction plan signing, orbit control data generation, orbit control program injection, and orbit control implementation monitoring.

[0004] However, in the existing technical solution, the processes of program scheduling, plan signing, and data generation all need to be carried out one after another after the orbit control strategy design is completed, resulting in a long preparation time for the orbit control implementation process. With the increasing number of targets in near-Earth space, the probability of collision is also gradually increasing. If the target temporarily maneuvers or maliciously approaches, the conventional target monitoring method may not be able to timely predict the dangerous target, and the existing solution cannot meet the demand for rapid implementation of spacecraft orbit control in emergency situations.

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

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

[0007] In a first aspect, the present application provides an orbit control planning generation method, and the technical solution of the method is as follows:

[0008] An orbit control instruction set containing all preset orbit control instructions of a target spacecraft during in-orbit flight is constructed, and a target orbit control strategy of the target spacecraft in a target sub-time period after a preset time is determined. The configuration information of each preset orbit control instruction includes: instruction basic parameters, instruction routing, spacecraft state, orbit control mode, and instruction timing.

[0009] According to the target starting route, the target spacecraft state and the target orbit control mode of the target spacecraft at a preset time, each preset orbit control instruction selected from the orbit control instruction set is determined as a first orbit control instruction to be executed in a target time period after the preset time, and the target time period includes the target sub-time period;

[0010] Based on the target orbit control strategy, the instruction basic parameters of the first orbit control instruction with the target starting time are corrected, and the instruction basic parameters of each first orbit control instruction are corrected based on the orbit control name of the target spacecraft in the target time period, to generate a target orbit control R sequence including a plurality of target orbit control instructions.

[0011] The orbit control planning generation method has the following advantages:

[0012] The method can reduce the time consumption of planning arrangement, signing, data generation and other orbit control preparation processes, and improve the efficiency of orbit control planning.

[0013] Based on the above scheme, the orbit control planning generation method can be further improved as follows.

[0014] In an optional manner, the instruction basic parameters include a starting time point, the target orbit control strategy includes start time parameters and shutdown time parameters of the target sub-time period, the starting time includes time constraints and no time constraints, and the target starting time is time-constrained.

[0015] The step of correcting the instruction basic parameters of the first orbit control instruction with the target starting time based on the target orbit control strategy includes:

[0016] The starting time point of the first orbit control instruction with time constraints is corrected based on the start time parameters and the shutdown time parameters of the target sub-time period.

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

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

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

[0020] For the target trajectory control instruction with time-constrained firing opportunity, the target trajectory control instructions are sorted according to the sequence of the firing time points and are controlled to be executed at the firing time points corresponding to the target sub-time period in sequence;

[0021] For the target trajectory control instruction with time-unconstrained firing opportunity and meeting the first preset condition, the target trajectory control instructions are sorted according to the sequence of the firing time points and are controlled to be executed before the target sub-time period in the target time period in sequence; wherein the first preset condition is that in all first trajectory control instructions, the firing time point is located before each first trajectory control instruction with time-constrained firing opportunity.

[0022] For the target trajectory control instruction with time-unconstrained firing opportunity and meeting the second preset condition, the target trajectory control instructions are sorted according to the sequence of the firing time points and are controlled to be executed after the target sub-time period in the target time period in sequence; wherein the second preset condition is that in all first trajectory control instructions, the firing time point is located after each first trajectory control instruction with time-constrained firing opportunity.

[0023] In an optional manner, the method further comprises:

[0024] Based on the target trajectory control R sequence, the target spacecraft is controlled in the target time period.

[0025] In a second aspect, the present application provides a trajectory control planning generation system, and the technical scheme of the system is as follows:

[0026] The system comprises a construction module, a processing module and a generation module.

[0027] The construction module is configured to construct a trajectory control instruction set containing all preset trajectory control instructions of the target spacecraft during on-orbit flight, and determine a target trajectory control strategy of the target spacecraft in a target sub-time period after a preset time; wherein the configuration information of each preset trajectory control instruction comprises instruction basic parameters, a firing route, a spacecraft state, a trajectory control mode and a firing opportunity.

[0028] The processing module is configured to determine each preset trajectory control instruction selected from the trajectory control instruction set as a first trajectory control instruction to be executed in a target time period after the preset time according to the target firing route, the target spacecraft state and the target trajectory control mode of the target spacecraft at the preset time; wherein the target time period contains the target sub-time period.

[0029] The generation module is configured to correct the instruction basic parameter of the first orbit control instruction with the target issuance time as the issuance time according to the target orbit control strategy, and correct the instruction basic parameter of each first orbit control instruction according to the orbit control name of the target spacecraft in the target time period, to generate a target orbit control R sequence including a plurality of target orbit control instructions.

[0030] The orbit control planning generation system has the following advantages:

[0031] The system can reduce the time consumption of planning arrangement, signing, data generation and other orbit control preparation processes, and improve the efficiency of orbit control planning.

[0032] Based on the above-mentioned scheme, the orbit control planning generation system can be further improved as follows.

[0033] In an optional manner, the instruction basic parameter includes an issuance time point, the target orbit control strategy includes an opening time parameter and a closing time parameter of the target sub-time period, the issuance time includes time constraints and no time constraints, the target issuance time is time-constrained, and the generation module is specifically configured to:

[0034] The issuance time point of the first orbit control instruction with time constraints is corrected based on the opening time parameter and the closing time parameter of the target sub-time period.

[0035] In an optional manner, the instruction basic parameter further includes an instruction code, and the generation module is specifically configured to:

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

[0037] In a third aspect, the technical scheme of an electronic device according to the present application is as follows:

[0038] The electronic device includes a memory, a processor, and a program stored in the memory and running on the processor, and the processor implements the steps of the orbit control planning generation method according to the present application when executing the program.

[0039] In a fourth aspect, the technical scheme of a computer readable storage medium according to the present application is as follows:

[0040] The computer readable storage medium stores instructions, and when the computer readable storage medium reads the instructions, the computer readable storage medium executes the steps of the orbit control planning generation method according to the present application.

[0041] The above description is only a summary of the technical solutions of the present application. In order to make the technical means of the present application more clearly understood and implemented according to the content of the specification, and in order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application are described below. BRIEF DESCRIPTION OF DRAWINGS

[0042] The accompanying drawings are included to provide a further understanding of the present application, and are incorporated in and constitute a part of this specification. The drawings illustrate embodiments of the present application and, together with the description, serve to explain the principles of the present application. In the drawings:

[0043] Figure 1 Flowchart of an embodiment of a trajectory control planning generation method of the present application;

[0044] Figure 2 Schematic diagram of a trajectory control R sequence configuration description interface;

[0045] Figure 3 Schematic diagram of a spacecraft state filling specification;

[0046] Figure 4 Schematic diagram of a trajectory control mode filling specification;

[0047] Figure 5 Schematic diagram of a launch timing filling specification;

[0048] Figure 6 Schematic diagram of a trajectory control R sequence menu;

[0049] Figure 7 Structural schematic diagram of an embodiment of a trajectory control planning generation system of the present application;

[0050] Figure 8 Structural schematic diagram of an embodiment of an electronic device of the present application. DETAILED DESCRIPTION

[0051] Exemplary embodiments of the present application will be described more fully hereinafter with reference to the accompanying drawings. While the present application is shown in the drawings and described as being implemented in an exemplary embodiment, it is to be understood that the present application is not limited to the embodiments set forth herein and that the embodiments set forth herein are not to be construed as limiting the scope of the present application.

[0052] Figure 1A flowchart of an embodiment of a trajectory control planning generation method provided by the present application is shown, which can be executed by electronic devices such as terminal devices or servers. 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 realize the trajectory control planning generation method by calling the computer readable instructions stored in the memory through the processor. As shown in Figure 1 the following steps are included:

[0053] S1, constructing a trajectory control instruction set containing all preset trajectory control instructions of a target spacecraft during its on-orbit flight, and determining a target trajectory control strategy of the target spacecraft within a target sub-time period after a preset time.

[0054] Among them, the target spacecraft is the spacecraft that needs to be controlled in this embodiment, and the specific spacecraft model is not limited here. The on-orbit flight period is the total time period of the on-orbit flight of the target spacecraft. The trajectory control instruction set refers to a set of instruction logic designed for on-orbit control of the spacecraft to ensure that it can autonomously or under control cope with all possible operating modes, fault scenarios and environmental changes in complex space environments. All preset trajectory control instructions include but are not limited to: ① routine operations: orbit adjustment, attitude control, payload switching, data transmission; ② emergency response: fault isolation, safety mode switching, redundant system activation; ③ environmental adaptation: plans to cope with radiation, temperature difference, and debris impact.

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

[0056] Among them, the preset time T k is set as the current time by default, and the target sub-time period is set as [T k+c ,T k+d ] by default; k, c and d are all constants, and the unit is min, for example [T k+120 ,T k+130 ]. The target trajectory control strategy is a trajectory control parameter file, which specifically contains the start time parameter and the shutdown time parameter of the target sub-time period.

[0057] It should be noted that the orbit control command set can be constructed before the spacecraft launch time T0, and the time point for determining when to start formulating the orbit control strategy is: preset time T0. k A previous target time point, which is usually T k-120 The time point for completing the formulation of the orbit control strategy is the preset time T. k Before.

[0058] S2. Based on the target command route, target spacecraft status, and target orbit control mode of the target spacecraft at the preset time, each preset orbit control command selected from the orbit control command set is determined as the first orbit control command to be executed in the target time period after the preset time.

[0059] The number of command routes is determined based on the actual situation, and may include, for example, a first command route, a second command route, and a third command route. The target command route is any one of these command routes. It should be noted that large spacecraft may have multiple telemetry and control receiving devices. The command direction is used to describe the target route for sending the command to the spacecraft, and different routes correspond to different methods of command transmission in the sequence.

[0060] The spacecraft state refers to the state of the spacecraft during its orbital flight. During orbital flight, the spacecraft adjusts its attitude and solar panels due to factors such as sunlight and temperature. There may be multiple attitude characteristics, each with different corresponding orbit control commands. Orbit control requires selecting the appropriate control command for each spacecraft state's different characteristics. In this embodiment, the spacecraft state by default includes: no characteristic, first characteristic, second characteristic, and third characteristic. Each preset orbit control command can correspond to at least one spacecraft state (except for the no characteristic).

[0061] The track control modes include time mode and speed mode, with target track control mode being one of them. Specifically: ① In time mode, the start-up time and shutdown time parameters in the track control parameter file are read, and the shutdown-related instructions in the R sequence are scheduled at a fixed time; ② In speed mode, the start-up time and target value of the track control speed increment are fixed values. After the track control is started, the cumulative speed increment of this track control is measured by measuring sensors such as accelerometers. When the cumulative value reaches the target value, the track control is automatically shut down. The shutdown instruction is scheduled at 1.1-1.5 times the start-up time (duration) as a backup shutdown method.

[0062] The first orbit control command is the preset orbit control command that simultaneously satisfies the target command route, target spacecraft status, and target orbit control mode among all preset orbit control commands. The target time period includes target sub-time periods, for example, the target time period is [T]. k+b ,T k+e ], where T k+aTo complete the generation of the target trajectory control R sequence, a < b < c, d < e.

[0063] S3, based on the target trajectory control strategy, the command basic parameters of the first trajectory control instruction with the target firing time are corrected, and the command basic parameters of each first trajectory control instruction are corrected based on the target trajectory control name of the target spacecraft in the target period, and a target trajectory control R sequence containing multiple target trajectory control instructions is generated.

[0064] Wherein, the firing time includes: time constraint and no time constraint; the target firing time is: time constraint. Part of the trajectory control instruction has no strict time constraint and is sent by manual control; part of the trajectory control instruction such as trajectory control switch instruction needs to read trajectory control parameter file and send according to strict time. The instructions in the trajectory control R sequence which are marked with sending time requirement (i.e. the trajectory control instructions with time constraint firing time) need to be sent according to the time agreed in the control parameter file.

[0065] It should be noted that the arrangement time of the shutdown instruction in the trajectory control R sequence corresponding to the two trajectory control modes (time mode and speed mode) is different, which needs to be selected according to the actual trajectory control mode. The trajectory control instruction set is configured with a trajectory control R sequence description interface, as shown in Figure 2 The trajectory control R sequence configuration description interface is described in XML format, and the interface filling specification includes:

[0066] ①The filling specification of the firing route is: "firing route" cannot be empty, and all firing routes of the spacecraft need to be listed and numbered in order of "1, 2, 3…". The "firing route" column of each trajectory control instruction in the trajectory control R sequence needs to be filled in accordance with the requirements.

[0067] ②The filling specification of the spacecraft state is: the filling format of "spacecraft state" is as shown in Figure 3 The parameters can be filled in "0" or "1", if "characteristics" is empty, fill in "1" in the "default" column; if any "characteristics" is filled in "1", fill in "0" or do not fill in the "default". If a certain trajectory control instruction in the trajectory control R sequence configuration outputs under a certain "characteristics" of "spacecraft state", fill in "1" in the corresponding "characteristics", as shown in Figure 3 Left; if multiple characteristics are output, fill in "1" at the same time, as shown in Figure 3 Middle; if the trajectory control instruction is independent of characteristics and is filled in "1" by default, the others are not filled in, as shown in Figure 3 Right.

[0068] ③The filling specification of the trajectory control mode is: the filling format of "trajectory control mode" is as shown in Figure 4As shown, the parameter can be filled with "0" or "1". If the track control instruction in the track control R sequence is used in speed mode, "speed mode" is filled with "1"; if it is used in time mode, "time mode" is filled with "1"; if the track control instruction is independent of the characteristics, it is not filled by default.

[0069] ④The filling standard of the command timing is as follows: Figure 5 As shown, in the track control R sequence, it is divided into "strict time constraint" and "no strict time constraint" instructions. The "strict time constraint" needs to be sent according to the strict time, such as the track control switch-on instruction, and the "no strict time constraint" is sent at any time as needed, such as the track control pre-state setting instruction, and the "default" column is filled with "1". The track control instructions in the track control R sequence marked with the sending timing requirement need to be sent according to the time agreed in the track control parameter interface.

[0070] In an optional manner, based on the target track control strategy, the step of modifying the instruction basic parameter of the first track control instruction with the target command timing includes:

[0071] Based on the start time parameter and the shutdown time parameter of the target sub-time period, the sending time point of the first track control instruction with time constraint is modified.

[0072] Among them, the sending time point of the first track control instruction with time constraint is modified as the start time parameter or the shutdown time parameter, which is determined according to the actual track control instruction.

[0073] In an optional manner, based on the track control name of the target spacecraft in the target time period, the step of modifying the instruction basic parameter of each first track control instruction includes:

[0074] The target field in the instruction code of each first track control instruction is replaced with the track control name of the target spacecraft in the target time period.

[0075] Among them, the track control name is "ABC", the instruction code of a certain first track 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 shown in the track control R sequence menu, the target route is selected as the first route (route 1), the spacecraft state is selected as the second feature (feature 2), and the track control mode is selected as the time mode, specifically: Figure 6

[0077] ①Select any "command route", and when generating the track control R sequence, automatically change the command route of each track control instruction in the sequence. ​

[0078] 2. Selecting "spacecraft state", when the instruction in the orbit control instruction set containing the "spacecraft state" attribute is consistent with the selection in the menu, output the orbit control instruction.

[0079] 3. Selecting "orbit control mode", when the instruction in the orbit control instruction set containing the "orbit control mode" attribute is consistent with the selection in the menu, output the orbit control instruction.

[0080] 4. Selecting the orbit control parameter file used in this orbit control in the "command opportunity" column, reading the start time parameter and the shutdown time parameter in the orbit control parameter file interface, and automatically correcting the sending time of the instruction containing the "orbit control mode" attribute. If the "orbit control mode" is "time mode", the shutdown related instruction in the orbit control R sequence is generated according to the shutdown time in the orbit control parameter file; if it is "speed mode", it is generated according to 1.1-1.5 times of the orbit control start time (duration) in the orbit control parameter file.

[0081] 5. Fill in the data name used in this orbit control in the "orbit control data" column, and automatically replace the orbit control data in the configuration with the data name input in the menu when generating the orbit control R sequence.

[0082] In an optional manner, the step of generating a target orbit control R sequence containing a plurality of target orbit control instructions includes:

[0083] For target orbit control instructions with time-constrained command opportunities, they are sorted in the order of the sending time points and are controlled to be executed at the sending time points corresponding to the target sub-time period in sequence.

[0084] For example, all target orbit control instructions are arranged in the order of the sending time points with serial numbers 01-10, and it is assumed that the target orbit control instructions with serial numbers 06 and 07 have time-constrained command opportunities, and the target orbit control instructions with the remaining serial numbers have time-unconstrained command opportunities. Then, the target orbit control instructions with serial numbers 06 and 07 are executed at the sending time points corresponding to the target sub-time period.

[0085] For target orbit control instructions with time-unconstrained command opportunities and meeting the first preset condition, they are sorted in the order of the sending time points and are controlled to be executed before the target sub-time period in the target time period.

[0086] For example, the target orbit control instructions with time-unconstrained command opportunities and meeting the first preset condition are the target orbit control instructions with serial numbers 01-05 in the above example, because the sending time points of the target orbit control instructions are located before each first orbit control instruction with time-constrained command opportunities in all first orbit control instructions.

[0087] The target sub-time period after the target time period is executed in sequence according to the target sub-time period.

[0088] The second preset condition is that, in all the first orbit control instructions, the time point of issuing is after the first orbit control instruction with time constraint.

[0089] In an optional mode, the method further comprises:

[0090] Based on the target orbit control R sequence, the target spacecraft is controlled in the target time period.

[0091] The target orbit control R sequence is sent in sequence according to the order of the target orbit control instructions in the target orbit control R sequence, the target orbit control instruction without time constraint is executed in the target time period, and the target orbit control instruction with time constraint is executed in the target sub-time period according to the plan until the orbit control is completed.

[0092] The technical scheme of the embodiment can reduce the time consumption of the orbit control preparation process such as plan arrangement, approval and data generation, and improve the efficiency of orbit control planning, and the method can be used as a backup means for emergency collision avoidance.

[0093] Figure 7 An embodiment of an orbit control planning generation system 200 provided by the application is shown in a structural schematic diagram. Figure 7 As shown in the figure, the system 200 comprises a construction module 210, a processing module 220 and a generation module 230.

[0094] The construction module 210 is configured to construct an orbit control instruction set comprising all preset orbit control instructions of a target spacecraft during on-orbit flight, and determine a target orbit control strategy of the target spacecraft in a target sub-time period after a preset time point.

[0095] The processing module 220 is configured to determine each preset orbit control instruction selected from the orbit control instruction set as a first orbit control instruction to be executed in a target time period after the preset time point according to the target issuing route, the target spacecraft state and the target orbit control mode of the target spacecraft at the preset time point.

[0096] The generation module 230 is configured to correct, based on the target orbit control strategy, the instruction basic parameter of the first orbit control instruction with the target firing time, and correct the instruction basic parameter of each first orbit control instruction based on the orbit control name of the target spacecraft in the target time period, to generate a target orbit control R sequence containing a plurality of target orbit control instructions.

[0097] In an optional manner, the instruction basic parameter comprises a firing time point, the target orbit control strategy comprises an opening time parameter and a closing time parameter of the target sub-time period, the firing time comprises a time constraint and a time constraint, the target firing time is a time constraint, and the generation module 230 is specifically configured to:

[0098] correct the firing time point of the first orbit control instruction with the time constraint based on the opening time parameter and the closing time parameter of the target sub-time period.

[0099] In an optional manner, the instruction basic parameter further comprises an instruction code, and the generation 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 generation module 230 is specifically configured to:

[0102] for the target orbit control instruction with the time constraint, the firing time point is sorted in the order and is sequentially controlled to be executed at the firing time point corresponding to the target sub-time period;

[0103] for the target orbit control instruction with the time constraint and meeting the first preset condition, the firing time point is sorted in the order and is sequentially controlled to be executed before the target sub-time period in the target time period; wherein the first preset condition is that in all first orbit control instructions, the firing time point is located before each first orbit control instruction with the time constraint;

[0104] for the target orbit control instruction with the time constraint and meeting the second preset condition, the firing time point is sorted in the order and is sequentially controlled to be executed after the target sub-time period in the target time period; wherein the second preset condition is that in all first orbit control instructions, the firing time point is located after each first orbit control instruction with the time constraint.

[0105] In an optional manner, further comprising 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 by the above embodiments are the same as those of the orbit control planning generation method, which will not be repeated here. In addition, when the system provided by the above embodiments implements its functions, only the division of the above functional modules is exemplified, and in actual application, the above functions can be completed by different functional modules according to needs, that is, the system is divided into different functional modules according to actual conditions to complete all or part of the above described functions. In addition, the system and method embodiments provided by the above embodiments belong to the same concept, and the specific implementation process is described in the method embodiments, which will not be repeated here.

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

[0109] In some embodiments, the orbit control planning generation system of the present application can be implemented in a combination of software and hardware, for example, the orbit control planning generation system of the present application can be a hardware decoding processor in the form of a processor programmed to execute the orbit control planning generation method of the present application, for example, the hardware decoding processor in the form of a processor can use one or more application specific integrated circuits (ASIC), DSP, programmable logic device (PLD), complex programmable logic device (CPLD), field programmable gate array (FPGA) or other electronic components.

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

[0111] The electronic device of the embodiment of the present application comprises a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor implements any one of the above-mentioned orbit control planning generation methods when executing the computer program, that is, the electronic device of the embodiment of the present application can include but is not limited to a processor and a memory; the memory is used for storing a computer program; and the processor is used for executing the orbit control planning generation method shown in any one of the embodiments of the present application by calling the computer program.

[0112] In an optional embodiment, an electronic device is provided, as shown in Figure 8 Figure 8 The electronic device 4000 shown in the embodiment of the present application comprises a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, for example, connected through a bus 4002. Optionally, the electronic device 4000 can further comprise a transceiver 4004, which can be used for data interaction, such as data sending and / or data receiving, between the electronic device and other electronic devices. It should be noted that the transceiver 4004 is not limited to one in actual application, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of the present application.

[0113] The processor 4001 can be a CPU (Central Processing Unit, central processor), 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 realize or execute various exemplary logical blocks, modules and circuits described in combination with the present disclosure. The processor 4001 can also be a combination of computing functions, such as one or more microprocessor combinations, combinations of DSP and microprocessor, etc.

[0114] The bus 4002 can include a path for transmitting information between the above-mentioned components. The bus 4002 can be a PCI (Peripheral Component Interconnect, peripheral component interconnect) bus or an EISA (Extended Industry Standard Architecture, extended industry standard architecture) bus, etc. The bus 4002 can be divided into an address bus, a data bus, a control bus, etc. For the convenience of representation, Figure 8 ​Only one bus 4002 is shown, but it could be comprised of several buses. Bus 4002 is used to transmit information between the various components within the computing device.

[0115] The memory 4003 can be a ROM (Read Only Memory) or other type of static storage device that can store static information and instructions; a RAM (Random Access Memory) or other type of dynamic storage device that can store information and instructions; an EEPROM (Electrically Erasable Programmable Read-Only Memory), a CD-ROM (Compact Disc Read-Only Memory) or other optical disk storage, a magnetic disk storage or other magnetic storage devices, or any other medium capable of storing desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited thereto.

[0116] The memory 4003 is used to store application program codes (computer programs) for implementing the solutions of the present application, and is controlled by the processor 4001 to execute. The processor 4001 is used to execute the application program codes stored in the memory 4003 to realize the contents shown in the foregoing method embodiments.

[0117] The electronic device can also be a terminal device, which can be any terminal device that can install an application and access a webpage 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 television, and a smart vehicle device.

[0118] It should be noted that, Figure 8 The electronic device shown is only an example and should not limit the functions and use range of the embodiments of the present application.

[0119] The computer readable storage medium of the embodiments of the present application, the computer readable storage medium stores a computer program, and the computer program is executed by the processor to realize any one of the above-mentioned orbit control planning generation methods.

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

[0121] In an example embodiment, a computer program product or computer program including computer instructions stored in a computer readable storage medium is also provided. A processor of an electronic device reads the computer instructions from the computer readable storage medium, and the processor executes the computer instructions to cause the electronic device to perform the above-mentioned trajectory planning generation method.

[0122] Computer program code for carrying out operations of the present application can be written in any combination of one or more programming languages, including an object oriented programming language such as Java, Smalltalk, C++ or the like and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code can execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the latter scenario, the remote computer can 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 the connection can be made to an external computer (for example, through the Internet using an Internet Service Provider).

[0123] It should be understood that the flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of various embodiments of the present application. In this regard, each block in the flowchart and block diagrams can represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical functions. It should also be noted that in some alternative implementations, the functions noted in the flowchart or block diagrams can occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently or the blocks can sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and / or flowchart illustrations, and combinations thereof, can be implemented by a dedicated hardware-based system that performs the specified functions or operations, or combinations of hardware and software.

[0124] The computer readable storage medium provided by the embodiments of the present application can be, but is not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or apparatus, or any combination of the above. More specific examples of the computer readable storage medium can include, but are not limited to, an electrical connection having one or more wires, a portable computer diskette, 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, the computer readable storage medium can be any tangible medium that contains or stores a program, which can be used by or in connection with an instruction execution system, apparatus or device.

[0125] The computer readable storage medium described above carries one or more programs, which, when executed by the electronic device, cause the electronic device to perform the methods shown in the embodiments described above.

[0126] The above description is merely the preferred embodiments of the present application and the explanation of the technical principles used. It should be understood by those skilled in the art that the disclosed scope of the present application is not limited to the technical solutions formed by the specific combinations of the technical features described above, and should also cover other technical solutions formed by any combinations of the technical features described above or their equivalent features without departing from the disclosed concept. For example, the technical solutions formed by replacing the above features with the technical features disclosed in the present application (but not limited to) having similar functions.

[0127] It should be noted that the terms "first", "second" and the like in the specification and claims of the present application are used to distinguish similar objects, and represent no specific order or sequential order. The order of use of similar objects can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described.

[0128] Those skilled in the art know that the present application can be implemented as a system, a method or a computer program product, so the present application can be specifically implemented as follows: it can be a complete hardware, a complete software (including firmware, resident software, microcode, etc.), or a combination of hardware and software, which is generally referred to as "circuit", "module" or "system" herein. In addition, in some embodiments, the present application can also be implemented as a computer program product in one or more computer readable media, which contains computer readable program code.

[0129] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary and are not to be construed as limiting the present application, and that changes, modifications, substitutions and variations can be made by those skilled in the art without departing from the scope of the present application.

Claims

1. A method for generating a trajectory control plan, characterized by, The method comprises the following steps: constructing a set of orbit control instructions containing all preset orbit control instructions of a target spacecraft during on-orbit flight of the target spacecraft, and determining a target orbit control strategy of the target spacecraft in a target sub-time period after a preset time point; wherein, the configuration information of each preset orbit control instruction comprises: instruction basic parameters, an instruction route, a spacecraft state, an orbit control mode, and an instruction time; determining each preset orbit control instruction screened from the set of orbit control instructions as a first orbit control instruction to be executed in a target time period after the preset time point according to the target instruction route, the target spacecraft state, and the target orbit control mode of the target spacecraft at the preset time point; wherein, the target time period contains the target sub-time period; based on the target orbit control strategy, modifying the instruction basic parameters of the first orbit control instruction with the target instruction time, and modifying the instruction basic parameters of each first orbit control instruction based on the orbit control name of the target spacecraft in the target time period, to generate a target orbit control R sequence containing a plurality of target orbit control instructions.

2. The method of claim 1, wherein, The instruction basic parameters comprise an instruction time point; the target orbit control strategy comprises an open time parameter and a close time parameter of the target sub-time period; the instruction time comprises time constraints and no time constraints; the target instruction time is time constraints; The step of modifying the instruction basic parameters of the first orbit control instruction with the target instruction time based on the target orbit control strategy comprises: based on the open time parameter and the close time parameter of the target sub-time period, modifying the instruction time point of the first orbit control instruction with time constraints.

3. The method of claim 2, wherein, The instruction basic parameters further comprise an instruction code; the step of modifying the instruction basic parameters of each first orbit control instruction based on the orbit control name of the target spacecraft in the target time period comprises: 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.

4. The method of claim 2, wherein, The step of generating a target orbit control R sequence containing a plurality of target orbit control instructions comprises: for the target orbit control instruction with time constraints, sorting in the order of instruction time points and sequentially controlling execution at the corresponding instruction time points in the target sub-time period; for the target orbit control instruction with no time constraints and meeting a first preset condition, sorting in the order of instruction time points and sequentially controlling execution before the target sub-time period in the target time period; wherein, the first preset condition is that, among all first orbit control instructions, the instruction time point is located before each first orbit control instruction with time constraints; for the target orbit control instruction with no time constraints and meeting a second preset condition, sorting in the order of instruction time points and sequentially controlling execution after the target sub-time period in the target time period; wherein, the second preset condition is that, among all first orbit control instructions, the instruction time point is located after each first orbit control instruction with time constraints.

5. The method of claim 1 to 4, wherein, The method further comprises the following steps: Based on the target orbit control R sequence, the target spacecraft is controlled in the target time period.

6. A trajectory planning generation system, characterized by, The method comprises: a construction module, a processing module and a generation module; The construction module is configured to construct an orbit control instruction set containing all preset orbit control instructions of the target spacecraft during on-orbit flight, and determine a 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 comprises instruction basic parameters, an order route, a spacecraft state, an orbit control mode and an order time; The processing module is configured to determine each preset orbit control instruction selected from the orbit control instruction set as a first orbit control instruction to be executed in a target time period after the preset time according to the target order route of the target spacecraft at the preset time, the target spacecraft state and the target orbit control mode; wherein the target time period contains the target sub-time period; The generation module is configured to correct the instruction basic parameters of the first orbit control instruction with the target order time as the order time based on the target orbit control strategy, and correct the instruction basic parameters of each first orbit control instruction based on the orbit control name of the target spacecraft in the target time period, to generate a target orbit control R sequence containing a plurality of target orbit control instructions.

7. The trajectory planning generation system of claim 6, wherein, The instruction basic parameters comprise an order time point; the target orbit control strategy comprises an open time parameter and a close time parameter of the target sub-time period; the order time comprises time constraints and no time constraints; the target order time is time constraints; and the generation module is specifically configured to: correct the order time point of the first orbit control instruction with time constraints based on the open time parameter and the close time parameter of the target sub-time period.

8. The trajectory planning generation system of claim 7, wherein, The instruction basic parameters further comprise an instruction code; and the generation module is specifically configured to: replace a 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.

9. An electronic device, comprising: The electronic device comprises a processor coupled with a memory, and the memory stores at least one computer program, which is loaded and executed by the processor to enable the electronic device to implement the orbit control planning generation method according to any one of claims 1 to 5.

10. A computer readable storage medium characterized by, The computer readable storage medium stores at least one computer program, which is loaded and executed by the processor to enable the computer readable storage medium to implement the orbit control planning generation method according to any one of claims 1 to 5.

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