Spacecraft measurement and control method, device, electronic equipment and storage medium

Abstract

The present disclosure provides a spacecraft measurement and control method, device, electronic device and storage medium, which relate to the field of spacecraft engineering technology. The spacecraft measurement and control method includes: obtaining a target measurement and control moment; the target measurement and control moment is the start moment of the measurement and control task, and the measurement and control task includes multiple measurement and control events; when the system moment reaches the target measurement and control moment, the measurement and control task is started; based on the target measurement and control moment, the time jump offset is determined; based on the time jump offset, the target execution moment of each measurement and control event is determined, and at the target execution moment, the spacecraft under the measurement and control task executes the corresponding measurement and control event. The present disclosure can flexibly adjust the time of the spacecraft measurement and control task through the time jump offset, thereby improving the efficiency of the measurement and control task. In addition, the target execution moment of each measurement and control event under the measurement and control task is determined by the time jump offset, which ensures the accuracy and synchronization of the time jump of each measurement and control event in the measurement and control task.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft engineering technology, and in particular to a spacecraft measurement and control method, device, electronic equipment and storage medium. Background Art

[0002] Spacecraft measurement and control refers to the process of monitoring, navigating, controlling and processing data of spacecraft through measurement and control means, covering multiple aspects such as orbit control, attitude control, acquisition and analysis of telemetry data, navigation and positioning, data transmission and communication, etc. Spacecraft measurement and control is of great significance in ensuring the normal operation of spacecraft and the smooth completion of space missions.

[0003] In the related technology, during the measurement and control of a spacecraft, after the measurement and control task of the current round is completed, it is necessary to wait for a long time before entering the measurement and control of the next round, which wastes a lot of time and has low test efficiency. Summary of the invention

[0004] In view of this, the embodiments of the present disclosure propose a spacecraft measurement and control method, device, electronic device and storage medium to solve the problem in the related art that, in the process of measuring and controlling a spacecraft, after the measurement and control task of the current round is completed, it is necessary to wait for a long time before entering the measurement and control of the next round, resulting in serious time waste and low testing efficiency.

[0005] According to a first aspect of the present disclosure, a spacecraft measurement and control method is provided, comprising: acquiring a target measurement and control moment; the target measurement and control moment is the start moment of a measurement and control task, the measurement and control task comprising a plurality of measurement and control events; when the system moment reaches the target measurement and control moment, starting the measurement and control task; determining a time hopping offset based on the target measurement and control moment; determining a target execution moment of each measurement and control event based on the time hopping offset, and executing the corresponding measurement and control event on the spacecraft under the measurement and control task at the target execution moment.

[0006] According to a second aspect of the present disclosure, there is provided a spacecraft measurement and control device, comprising: a preparation module, used to obtain a target measurement and control moment; the target measurement and control moment is the start moment of a measurement and control task, the measurement and control task comprising a plurality of measurement and control events; a start module, used to start the measurement and control task when the system moment reaches the target measurement and control moment; a processing module, used to determine a time jump offset based on the target measurement and control moment; a measurement and control module, used to determine a target execution moment of each measurement and control event based on the time jump offset, and execute the corresponding measurement and control event on the spacecraft under the measurement and control task at the target execution moment.

[0007] According to a third aspect of the present disclosure, there is provided an electronic device, comprising: a processor; and a memory storing a program, wherein the program comprises instructions, and the instructions, when the processor is running, enable the processor to execute the above-mentioned spacecraft measurement and control method.

[0008] According to a fourth aspect of the present disclosure, a non-transitory computer-readable storage medium storing computer instructions is provided, wherein the computer instructions are used to enable the computer to execute the above-mentioned spacecraft measurement and control method.

[0009] The exemplary embodiments of the present disclosure may have some or all of the following beneficial effects:

[0010] In the spacecraft measurement and control method provided in the example implementation of the present disclosure, a target measurement and control moment is obtained; the target measurement and control moment is the start moment of the measurement and control task, and the measurement and control task includes multiple measurement and control events; when the system moment reaches the target measurement and control moment, the measurement and control task is started; based on the target measurement and control moment, a time jump offset is determined; based on the time jump offset, a target execution moment of each measurement and control event is determined, and at the target execution moment, the corresponding measurement and control event is executed on the spacecraft under the measurement and control task. The embodiment of the present disclosure achieves the self-start of the measurement and control task by obtaining the target measurement and control moment and starting the measurement and control task when the system moment reaches the target measurement and control moment; further, by determining the time jump offset through the target measurement and control moment, the execution time of each measurement and control event in the measurement and control task can be flexibly adjusted based on the time jump offset, thereby improving the measurement and control efficiency and ensuring the accuracy and synchronization of the time jumps of each measurement and control event during the measurement and control task.

[0011] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Further details, features and advantages of the present disclosure are disclosed in the following description of exemplary embodiments in conjunction with the accompanying drawings, in which:

[0013] Figure 1 A flow chart of a spacecraft measurement and control method according to an exemplary embodiment of the present disclosure is shown;

[0014] Figure 2 A functional structure diagram of a spacecraft measurement and control system according to an exemplary embodiment of the present disclosure is shown;

[0015] Figure 3 A schematic block diagram of a spacecraft measurement and control device according to an exemplary embodiment of the present disclosure is shown;

[0016] Figure 4 A structural block diagram of an exemplary electronic device that can be used to implement the embodiments of the present disclosure is shown. DETAILED DESCRIPTION

[0017] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0018] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0019] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0020] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0021] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0022] The embodiments of the present disclosure provide a spacecraft measurement and control method, device, electronic device and storage medium. The following describes the scheme of the present disclosure with reference to the accompanying drawings for illustration.

[0023] The present disclosure first provides a spacecraft measurement and control method. Figure 1 As shown, the spacecraft measurement and control method specifically includes the following steps:

[0024] S110: Obtaining a target measurement and control time; the target measurement and control time is the start time of the measurement and control task, and the measurement and control task includes multiple measurement and control events;

[0025] S120: When the system time reaches the target measurement and control time, start the measurement and control task;

[0026] S130: Determine a time-hopping offset based on the target measurement and control time;

[0027] S140: Determine the target execution time of each measurement and control event based on the time hopping offset, and execute the corresponding measurement and control event on the spacecraft under the measurement and control task at the target execution time.

[0028] The spacecraft measurement and control method provided in the embodiment of the present disclosure realizes the self-starting of the measurement and control task by acquiring the target measurement and control moment and starting the measurement and control task when the system moment reaches the target measurement and control moment; further, the time jump offset is determined by the target measurement and control moment, so that the execution time of each measurement and control event in the measurement and control task can be flexibly adjusted based on the time jump offset, thereby improving the measurement and control efficiency and ensuring the accuracy and synchronization of the time jumps of each measurement and control event during the measurement and control task.

[0029] Next, in another embodiment, the above steps are described in more detail.

[0030] In step S110, a target measurement and control time is obtained; the target measurement and control time is the start time of the measurement and control task, and the measurement and control task includes multiple measurement and control events.

[0031] In the embodiments of the present application, the measurement and control tasks refer to the process of monitoring, navigating, controlling and processing data of a spacecraft by means of measurement and control. For example, the measurement and control tasks may include the measurement and control of the orbit control, attitude control, acquisition and analysis of telemetry data, navigation and positioning, data transmission and communication of the spacecraft.

[0032] In the embodiment of the present application, the above-mentioned measurement and control tasks may include multiple measurement and control events. For example, the above-mentioned measurement and control events may include important events related to the spacecraft such as verifying the satellite status, satellite-to-ground link status, attitude and orbit control adjustment, remote control command, data upload, etc.

[0033] In the embodiment of the present application, illustratively, the above-mentioned measurement and control task can be a test task based on the joint debugging target in the spacecraft full-hosting service. Specifically, the above-mentioned test task based on the joint debugging target refers to the provider of the spacecraft full-hosting service (here, the spacecraft measurement and control service provider) as the general controller of the measurement and control task, organizing the spacecraft developer and the spacecraft user to conduct multiple rounds of joint debugging tests in strict accordance with the spacecraft flight procedure to verify the satellite status, satellite-to-ground link status, attitude and orbit control adjustment, remote control command, data injection and other important satellite events.

[0034] In the embodiments of the present application, the above-mentioned spacecraft refers to various types of aircraft that operate in space according to the laws of celestial mechanics and perform specific tasks such as exploring, developing, and utilizing space and celestial bodies. For example, the above-mentioned spacecraft may be a space vehicle such as a satellite, a probe, or a rocket.

[0035] In the embodiment of the present application, the target measurement and control time is the start time of the measurement and control task. For example, the target measurement and control time can be set to any time as needed. For example, it can be a time before or after the current time.

[0036] In the embodiment of the present application, the above-mentioned acquisition of the target measurement and control moment can be implemented as follows: receiving the user's setting operation, and determining the target measurement and control moment based on the setting operation. Specifically, the above-mentioned user is a manager who can manage the measurement and control task, and the manager can input the target measurement and control moment set according to actual needs through the configuration management service provided by the spacecraft measurement and control system. Among them, the above-mentioned spacecraft measurement and control system is a system for executing the spacecraft measurement and control method provided in the embodiment of the present application.

[0037] In step S120, when the system time reaches the target measurement and control time, the measurement and control task is started.

[0038] In the embodiment of the present application, the above-mentioned system time is the system time of the above-mentioned spacecraft measurement and control system.

[0039] In the embodiment of the present application, the above-mentioned starting the measurement and control task when the system time reaches the target measurement and control time can be implemented illustratively as follows: adjusting the system time to the preparatory measurement and control time; the preparatory measurement and control time is later than the current time and earlier than the target measurement and control time; when it is detected that the system time reaches the target measurement and control time, starting the measurement and control task. Specifically, assuming that the above-mentioned target measurement and control time is set to 13:24:56 on December 24, 2024, the system time of the spacecraft measurement and control system can be set to 13:20:00 on December 24, 2024. Then, after 4 minutes and 56 seconds, the system time reaches the target measurement and control time, and the spacecraft measurement and control system automatically starts the measurement and control task.

[0040] In an embodiment of the present application, the system time of the spacecraft measurement and control system is adjusted to the preparation measurement and control time according to actual needs, so that the measurement and control task can be automatically started when the system time reaches the target measurement and control time.

[0041] In step S130, a time jump offset is determined based on the target measurement and control time.

[0042] In the embodiment of the present application, the time-hopping offset is determined based on the target measurement and control moment. Exemplarily, it can be implemented as follows: the difference between the target measurement and control moment and the current moment is calculated to obtain the time-hopping offset. That is, the time-hopping offset can be the difference between the current moment and the target measurement and control moment. Preferably, the accuracy of the time-hopping offset is set to the second level.

[0043] In an embodiment of the present application, taking the completion time of the measurement and control mission of the current circle of the spacecraft as 14:05:06 on December 24, 2024, the current time is 14:10:05 on December 24, 2024, the original start time of the measurement and control mission of the next circle is 15:35:06 on December 24, 2024, and the waiting time is one and a half hours as an example, the target measurement and control time of the measurement and control mission of the next circle can be set to 15:30:06 on December 24, 2024. The time jump offset is 1 hour, 20 minutes and 01 seconds, and the waiting time is half an hour, which is used to prepare for the measurement and control mission.

[0044] When performing joint debugging and measurement and control of a spacecraft, usually after completing the measurement and control task of the current round, it is necessary to wait for a long time interval before entering the measurement and control task of the next round, which wastes time seriously and has low joint debugging efficiency. The embodiment of the present application sets the above-mentioned time jump offset, and further, the current time can be jumped to the target measurement and control time through the above-mentioned time jump offset, thereby avoiding long waiting times, realizing flexible adjustment of the measurement and control task time of the spacecraft, and improving the accuracy and efficiency of the measurement and control task.

[0045] In step S140, the target execution time of each measurement and control event is determined based on the time hopping offset, and the corresponding measurement and control event is executed on the spacecraft under the measurement and control task at the target execution time.

[0046] In an embodiment of the present application, in order to ensure the accuracy and synchronization of the time hopping of each measurement and control event in the measurement and control task, after determining the time hopping offset through the above steps, the embodiment of the present application can further perform the following operations: publish a time hopping change event so that each measurement and control event obtains the time hopping offset by subscribing to the time hopping change event.

[0047] In the embodiment of the present application, after obtaining the time-hopping offset, each measurement and control event can determine the target execution time based on the obtained time-hopping offset. Exemplarily, the process can be implemented as follows: obtaining the time when the measurement and control event reads the time-hopping change event; based on the reading time and the time-hopping offset, determining the target execution time of each measurement and control event. The time when the measurement and control event reads the time-hopping change event is the time when the measurement and control event reads the time-hopping change event published by the spacecraft measurement and control system based on the subscription service.

[0048] Specifically, after the above-mentioned measurement and control events read the time jump offset, the time jump offset read from the current moment needs to be jumped back. For example, the automatic orbit determination acquires telemetry data and adds the time jump offset processing logic; the remote control command comparison and successful execution time is set according to the time after the time jump; the submission time of the remote control injection data uses the time after the time jump; the small loop adds the time jump offset; the entry and update time of the measurement and control plan adds the time jump offset; the automated scheduling is triggered according to the time after the time jump; the execution time in the scheduling log adds the time jump offset; when the health diagnosis process responds, the response time adds the time jump offset; the telemetry adds the time jump offset; the external measurement adds the time jump offset, etc.

[0049] Next, combine Figure 2 The functional structure of the above-mentioned spacecraft measurement and control system and the data flow of the time jump offset are explained, among which: Figure 2 The functional structure diagram of the above-mentioned spacecraft measurement and control system is as follows:

[0050] like Figure 2 As shown, the managers of the spacecraft measurement and control tasks set the time hop and publish the time hop change event through the spacecraft measurement and control system configuration management service. The measurement and control services related to the time hop in the spacecraft measurement and control system read the time hop offset in the configuration management service by subscribing to the time hop change event, and add the time hop offset to the time setting corresponding to the measurement and control services related to the time hop according to the time hop offset, so as to execute the corresponding measurement and control services based on the time setting with the time hop offset, and save the measurement and control results.

[0051] Exemplarily, the modules related to measurement and control in the spacecraft measurement and control system may include a control calculation module, a remote control command module, a telemetry outer module, a measurement and control plan management module, and a health diagnosis module. Among them, the services affected by time jump in the control calculation module include automatic orbit determination and control measurement and control; the services affected by time jump in the remote control command module include remote control injection data, remote control command, and small ring time; the services affected by time jump in the telemetry outer module include telemetry processing time and outer processing time; the services affected by time jump in the measurement and control plan management module include measurement and control plan time update and automatic scheduling; the services affected by time jump in the health diagnosis module include response time.

[0052] In addition, managers of the above-mentioned spacecraft measurement and control tasks can also set time hopping according to spacecraft based on the spacecraft measurement and control system configuration management service to bind the time hopping with the measurement and control task, thereby ensuring that the time hopping is only for the spacecraft associated with the current measurement and control task and has no impact on spacecraft outside the measurement and control task.

[0053] The spacecraft measurement and control method provided in the embodiment of the present disclosure realizes the self-starting of the measurement and control task by acquiring the target measurement and control moment and starting the measurement and control task when the system moment reaches the target measurement and control moment; further, the time jump offset is determined by the target measurement and control moment, so that the execution time of each measurement and control event in the measurement and control task can be flexibly adjusted based on the time jump offset, thereby improving the measurement and control efficiency and ensuring the accuracy and synchronization of the time jumps of each measurement and control event during the measurement and control task.

[0054] The above mainly introduces the solution provided by the embodiment of the present invention from the perspective of the method. In order to achieve the above functions, it includes hardware structures and / or software modules corresponding to the execution of each function. Those skilled in the art should easily realize that, in combination with the units and algorithm steps of each example described in the embodiments disclosed herein, the present invention can be implemented in the form of hardware or a combination of hardware and computer software. Whether a function is executed in the form of hardware or computer software driving hardware depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of the present invention.

[0055] The embodiment of the present invention can divide the functional modules of the spacecraft measurement and control device according to the above method example. For example, each functional module can be divided according to each function, or two or more functions can be integrated into one processing module. The above integrated module can be implemented in the form of hardware or in the form of software functional modules. It should be noted that the division of modules in the embodiment of the present invention is schematic and is only a logical functional division. There may be other division methods in actual implementation.

[0056] Accordingly, the embodiment of the present disclosure also provides a spacecraft measurement and control device. Figure 3 As shown, the spacecraft measurement and control device 300 may include a preparation module 310, a start module 320, a processing module 330 and a measurement and control module 340, wherein:

[0057] The preparation module 310 can be used to obtain a target measurement and control time; the target measurement and control time is the start time of the measurement and control task, and the measurement and control task includes multiple measurement and control events;

[0058] The start module 320 can be used to start the measurement and control task when the system time reaches the target measurement and control time;

[0059] The processing module 330 may be used to determine a time hopping offset based on a target measurement and control time;

[0060] The measurement and control module 340 can be used to determine the target execution time of each measurement and control event based on the time hopping offset, and execute the corresponding measurement and control event on the spacecraft under the measurement and control task at the target execution time.

[0061] In the embodiment of the present application, the above-mentioned preparation module is specifically used to obtain the target measurement and control time through the following process: receiving the user's setting operation, and determining the target measurement and control time based on the setting operation.

[0062] In an embodiment of the present application, the above-mentioned starting module is specifically used to start the measurement and control task when the system time reaches the target measurement and control time through the following process: adjust the system time to the preparatory measurement and control time; the preparatory measurement and control time is later than the current time and earlier than the target measurement and control time; when it is detected that the system time reaches the target measurement and control time, start the measurement and control task.

[0063] In an embodiment of the present application, the above-mentioned processing module is specifically used to determine the time-hopping offset based on the target measurement and control time through the following process: calculating the difference between the target measurement and control time and the current time to obtain the time-hopping offset.

[0064] In an embodiment of the present application, the above-mentioned spacecraft measurement and control device also includes a publishing module, which is specifically used to: after determining the time hopping offset based on the target measurement and control time, publish a time hopping change event so that each measurement and control event obtains the time hopping offset by subscribing to the time hopping change event; the time hopping change event includes the time hopping offset.

[0065] In an embodiment of the present application, the above-mentioned measurement and control module is specifically used to realize the determination of the target execution time of each measurement and control event based on the time jump offset through the following process: obtaining the moment when the measurement and control event reads the time jump change event; based on the moment when the measurement and control event reads the time jump change event and the time jump offset, determining the target execution time of each measurement and control event.

[0066] In the embodiment of the present application, the processing module is further used to: after determining the time hopping offset based on the target measurement and control time, establish an association relationship between the time hopping offset and the spacecraft under the measurement and control task. That is, the time hopping is only for the spacecraft associated with the current measurement and control task, and has no effect on the spacecraft outside the measurement and control task.

[0067] In addition, the specific implementation details of the above-mentioned spacecraft measurement and control device have been described in detail in the corresponding position of the spacecraft measurement and control method, so they will not be repeated here.

[0068] Figure 4 Schematic diagram of the structure of an electronic device in the embodiment of the present disclosure. Figure 4 , which shows a structural schematic diagram of an electronic device 400 suitable for implementing the embodiments of the present disclosure. Figure 4The electronic device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present disclosure.

[0069] like Figure 4 As shown, the electronic device 400 may include a processing device (e.g., a central processing unit, a graphics processing unit, etc.) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage device 408 to a random access memory (RAM) 403 to implement the spacecraft measurement and control method of the embodiment described in the present disclosure. Various programs and data required for the operation of the electronic device 400 are also stored in the RAM 403. The processing device 401, the ROM 402, and the RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0070] Typically, the following devices may be connected to the I / O interface 405: an input device 406 including, for example, a touch screen, a touch pad, a keyboard, a mouse, a camera, a microphone, an accelerometer, a gyroscope, etc.; an output device 407 including, for example, a liquid crystal display (LCD), a speaker, a vibrator, etc.; a storage device 408 including, for example, a magnetic tape, a hard disk, etc.; and a communication device 409. The communication device 409 may allow the electronic device 400 to communicate with other devices wirelessly or by wire to exchange data. Although Figure 4 The electronic device 400 is shown with various devices, but it should be understood that it is not required to implement or possess all the devices shown. More or fewer devices may be implemented or possessed instead.

[0071] In particular, according to an embodiment of the present disclosure, the process described above with reference to the flowchart can be implemented as a computer software program. For example, an embodiment of the present disclosure includes a computer program product, which includes a computer program carried on a non-transitory computer-readable medium, and the computer program contains program code for executing the method shown in the flowchart, thereby implementing the spacecraft measurement and control method as described above. In such an embodiment, the computer program can be downloaded and installed from the network through the communication device 409, or installed from the storage device 408, or installed from the ROM402. When the computer program is executed by the processing device 401, the above functions defined in the method of the embodiment of the present disclosure are executed.

[0072] It should be noted that the computer-readable medium disclosed above may be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media 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 disclosure, a computer-readable storage medium may be any tangible medium containing or storing a program that may be used by or in combination with an instruction execution system, device or device. In the present disclosure, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, in which a computer-readable program code is carried. This propagated data signal may take a variety of forms, including but not limited to an electromagnetic signal, an optical signal, or any suitable combination of the above. The computer readable signal medium may also be any computer readable medium other than a computer readable storage medium, which may send, propagate or transmit a program for use by or in conjunction with an instruction execution system, apparatus or device. The program code contained on the computer readable medium may be transmitted using any suitable medium, including but not limited to: wires, optical cables, RF (radio frequency), etc., or any suitable combination of the above.

[0073] In some embodiments, the client and the server may communicate using any currently known or future developed network protocol such as HTTP (Hyper Text Transfer Protocol), and may be interconnected with any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include a local area network ("LAN"), a wide area network ("WAN"), an internet (e.g., the Internet), and a peer-to-peer network (e.g., an ad hoc peer-to-peer network), as well as any currently known or future developed network.

[0074] The computer-readable medium may be included in the electronic device, or may exist independently without being installed in the electronic device.

[0075] The computer-readable medium carries one or more programs. When the one or more programs are executed by the electronic device, the electronic device:

[0076] Obtaining the target measurement and control time; the target measurement and control time is the start time of the measurement and control task, and the measurement and control task includes multiple measurement and control events;

[0077] When the system time reaches the target measurement and control time, the measurement and control task is started;

[0078] Determine the time-hopping offset based on the target measurement and control time;

[0079] The target execution time of each measurement and control event is determined based on the time hopping offset, and the corresponding measurement and control event is executed on the spacecraft under the measurement and control mission at the target execution time.

[0080] Optionally, when the above one or more programs are executed by the electronic device, the electronic device may also execute other steps described in the above embodiments.

[0081] Computer program code for performing the operations of the present disclosure may be written in one or more programming languages ​​or a combination thereof, including, but not limited to, object-oriented programming languages, such as Java, Smalltalk, C++, and conventional procedural programming languages, such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving 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 may be connected to an external computer (e.g., through the Internet using an Internet service provider).

[0082] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present disclosure. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0083] The units involved in the embodiments described in the present disclosure may be implemented by software or hardware, wherein the name of a unit does not, in some cases, constitute a limitation on the unit itself.

[0084] The functions described above herein may be performed at least in part by one or more hardware logic components. For example, without limitation, exemplary types of hardware logic components that may be used include: field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chips (SOCs), complex programmable logic devices (CPLDs), and the like.

[0085] In the context of the present disclosure, a machine-readable medium may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. A machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or equipment, or any suitable combination of the foregoing. A more specific example of a machine-readable storage medium may include an electrical connection based on one or more lines, 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 foregoing.

[0086] The above description is only a preferred embodiment of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, the above features are replaced with the technical features with similar functions disclosed in the present disclosure (but not limited to) by each other to form a technical solution.

[0087] In addition, although each operation is described in a specific order, this should not be understood as requiring these operations to be performed in the specific order shown or in a sequential order. Under certain circumstances, multitasking and parallel processing may be advantageous. Similarly, although some specific implementation details are included in the above discussion, these should not be interpreted as limiting the scope of the present disclosure. Some features described in the context of a separate embodiment can also be implemented in a single embodiment in combination. On the contrary, the various features described in the context of a single embodiment can also be implemented in multiple embodiments individually or in any suitable sub-combination mode.

[0088] Although the subject matter has been described in language specific to structural features and / or methodological logical actions, it should be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or actions described above. On the contrary, the specific features and actions described above are merely example forms of implementing the claims.

Claims

1. A spacecraft measurement and control method, characterized in that: include: Obtaining a target measurement and control time; the target measurement and control time is the start time of the measurement and control task, and the measurement and control task includes multiple measurement and control events; When the system time reaches the target measurement and control time, starting the measurement and control task; Determining a time-hopping offset based on the target measurement and control time; The target execution time of each of the measurement and control events is determined based on the time jump offset, and the corresponding measurement and control event is executed on the spacecraft under the measurement and control task at the target execution time.

2. The spacecraft measurement and control method according to claim 1, characterized in that: The obtaining of the target measurement and control time comprises: A setting operation of a user is received, and the target measurement and control time is determined based on the setting operation.

3. The spacecraft measurement and control method according to claim 1, characterized in that: When the system time reaches the target measurement and control time, starting the measurement and control task includes: Adjusting the system time to a preparatory measurement and control time; the preparatory measurement and control time is later than the current time and earlier than the target measurement and control time; When it is detected that the system moment reaches the target measurement and control moment, the measurement and control task is started.

4. The spacecraft measurement and control method according to claim 1, characterized in that: The determining of the time hopping offset based on the target measurement and control time comprises: The difference between the target measurement and control time and the current time is calculated to obtain the time jump offset.

5. The spacecraft measurement and control method according to claim 4, characterized in that: After determining the time hopping offset based on the target measurement and control time, the method further includes: A time hopping change event is published, so that each of the measurement and control events obtains the time hopping offset by subscribing to the time hopping change event; the time hopping change event includes the time hopping offset.

6. The spacecraft measurement and control method according to claim 5, characterized in that: The determining the target execution time of each of the measurement and control events based on the time hopping offset includes: Obtaining the moment when the measurement and control event reads the time jump change event; Based on the time when the time jump change event is read from the measurement and control event and the time jump offset, the target execution time of each measurement and control event is determined.

7. The spacecraft measurement and control method according to any one of claims 1 to 6, characterized in that: After determining the time hopping offset based on the target measurement and control time, the method further includes: Establish an association relationship between the time jump offset and the spacecraft under the measurement and control mission.

8. A spacecraft measurement and control device, characterized in that: include: A preparation module is used to obtain a target measurement and control time; the target measurement and control time is the start time of the measurement and control task, and the measurement and control task includes multiple measurement and control events; A starting module, used to start the measurement and control task when the system time reaches the target measurement and control time; A processing module, used to determine a time-hopping offset based on the target measurement and control time; The measurement and control module is used to determine the target execution time of each measurement and control event based on the time jump offset, and execute the corresponding measurement and control event on the spacecraft under the measurement and control task at the target execution time.

9. An electronic device, comprising: processor; and a memory storing a program, wherein the program comprises instructions for causing the processor to execute the method according to any one of claims 1-7.

10. A non-transitory computer-readable storage medium storing computer instructions, wherein: The computer instructions are used to cause the computer to execute the method according to any one of claims 1-7.

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