Satellite orbit control shutdown methods, electronic equipment, storage media and software products

Abstract

This application provides a satellite orbit control shutdown method, electronic device, storage medium, and program product, including determining the orbit control duration based on orbit control data packets, and determining whether the orbit control duration is less than an orbit control duration threshold; if the orbit control duration is less than the orbit control duration threshold, selecting a first strategy to control the satellite to execute the current orbit control task, wherein the first strategy includes: recording the power-on duration from the power-on time of the current orbit control task; if the power-on duration is greater than or equal to the first duration threshold, generating a shutdown command to terminate the current orbit control task; if the orbit control duration is greater than or equal to the orbit control duration threshold, selecting a second strategy to control the satellite to execute the current orbit control task, wherein the second strategy includes: calculating the target velocity increment of the satellite; if the target velocity increment is greater than or equal to a velocity increment threshold and the power-on duration is greater than or equal to the second duration threshold, generating a shutdown command to terminate the current orbit control task.

Description

Technical Field

[0001] This invention relates primarily to the field of satellite orbit control technology, and more particularly to a satellite orbit control shutdown method, electronic equipment, storage medium, and program product. Background Technology

[0002] During orbit control execution, the duration of the satellite's thrusters' operation directly impacts the final orbit control effectiveness. Typically, the satellite calculates the velocity increment based on measurements from individual velocity increment measurement units (such as accelerometers), and autonomously triggers thruster shutdown when the target velocity increment is reached. However, this method places high demands on the accuracy and reliability of these measurement units. If a measurement unit experiences operational problems during the critical mission window, it could lead to an anomaly in a single orbit control attempt, thereby affecting the overall mission success or failure. Summary of the Invention

[0003] The purpose of this invention is to provide a satellite orbit control shutdown method, electronic device, storage medium, and program product, which determines the generation time of shutdown command by selecting an appropriate strategy, thereby ensuring orbit control safety and mission safety.

[0004] In a first aspect, a satellite orbit control shutdown method is provided, comprising: The track control duration is determined based on the track control data packet, and it is determined whether the track control duration is less than the track control duration threshold. If the orbit control duration is less than the orbit control duration threshold, a first strategy is selected to control the satellite to perform the current orbit control task, wherein the first strategy includes: Starting from the start time of the current orbit control mission, record the start time, where the start time is the working time of the satellite's thrusters after they start jetting. If the power-on duration is greater than or equal to the first duration threshold, a power-off command is generated to terminate the current track control task; If the orbit control duration is greater than or equal to the orbit control duration threshold, a second strategy is selected to control the satellite to perform the current orbit control task, wherein the second strategy includes: Calculate the target velocity increment of the satellite; Record the startup duration starting from the startup time of the current track control task; If the target speed increment is greater than or equal to the speed increment threshold and the power-on duration is greater than or equal to the second duration threshold, a power-off command is generated to terminate the current track control task.

[0005] In some embodiments, recording the power-on duration includes: Starting from the moment the satellite receives the injection command, calculate the jetting duration of the thruster in each control cycle corresponding to the current orbit control mission; The total jet duration is obtained by summing the jet durations within each control cycle. The jet duration of a single thruster is obtained as the start-up duration based on the total jet duration and the number of thrusters used.

[0006] In some embodiments, the satellite is equipped with a quartz accelerometer, and the calculation of the target velocity increment of the satellite includes: From the moment the satellite receives the injection command, the first velocity increment generated by the thruster in each control cycle corresponding to the current orbit control mission is calculated based on the first acceleration output data of the quartz accelerometer in the satellite's own system. The target velocity increment of the satellite is obtained by summing the first velocity increments generated in each control cycle.

[0007] In some embodiments, the satellite is equipped with an inertial accelerometer, and calculating the target velocity increment of the satellite includes: From the moment the satellite receives the injection command, the second velocity increment generated by the thruster in each control cycle corresponding to the current orbit control mission is calculated based on the second acceleration output data of the inertial accelerometer in the X direction of the satellite's own system. The target velocity increment of the satellite is obtained by summing the second velocity increments generated in each control cycle.

[0008] In some embodiments, the satellite is equipped with a quartz accelerometer and an inertial measurement unit (IMU), and the calculation of the target velocity increment of the satellite includes: Based on the accelerometer status information and / or priority information, select one of the quartz accelerometer and the inertial measurement accelerometer as the target accelerometer; The target accelerometer is used to collect the corresponding target acceleration output data, and the target velocity increment of the satellite is calculated based on the target acceleration output data.

[0009] In some embodiments, after calculating the target velocity increment of the satellite, the method further includes: The effectiveness of the target velocity increment is determined based on the cross-verification mechanism between the quartz accelerometer and the inertial accelerometer. If the target velocity increment is determined to be invalid, the satellite is controlled to continue performing the current orbit control task.

[0010] In some embodiments, the first duration threshold is 50 seconds; the second duration threshold is 80% multiplied by the track control duration.

[0011] In a second aspect, an electronic device is provided. This device includes: one or more processors; and one or more memories coupled to the one or more processors and storing instructions thereon. When the instructions are executed individually or jointly by the one or more processors, the electronic device performs the aforementioned satellite orbit control shutdown method.

[0012] In a third aspect, a non-transitory computer-readable storage medium is provided that stores machine-executable instructions. When executed by one or more processors of a machine, the machine-executable instructions cause the machine to perform any of the methods described above.

[0013] In a fourth aspect, a computer program product including machine-executable instructions is provided. When executed by one or more processors of a machine, the machine-executable instructions cause the machine to perform any of the methods described above.

[0014] Compared with the prior art, the present invention has the following advantages: This application provides a satellite orbit control shutdown method, electronic device, storage medium, and program product. It selects either a first strategy or a second strategy to control the satellite to perform the current orbit control task based on the orbit control duration. The first strategy determines whether to generate a shutdown command based on the power-on duration, while the second strategy determines whether to generate a shutdown command based on the power-on duration and speed increment. Thus, for different orbit control tasks (such as short-term and long-term orbit control tasks), a more suitable shutdown strategy can be selected to improve the reliability of the shutdown command, thereby ensuring orbit control safety and mission safety.

[0015] It should be understood that the summary section is not intended to identify key or essential features of the embodiments of this disclosure, nor is it intended to limit the scope of this disclosure. Other features of this disclosure will become readily apparent from the following description. Attached Figure Description

[0016] The accompanying drawings are included to provide a further understanding of this application; they are incorporated into and constitute a part of this application. The drawings illustrate embodiments of this application and, together with this specification, serve to explain the principles of this application. In the drawings: Figure 1 A flowchart illustrating an exemplary satellite orbit control shutdown method provided in this application is shown; Figure 2 This application provides an exemplary logical diagram illustrating the orbit control execution process of a satellite. Figure 3 A schematic diagram of an electronic device provided by example in this application is shown. Detailed Implementation

[0017] The principles of this disclosure will now be described with reference to some embodiments. It should be understood that these embodiments are described for illustrative purposes only and to assist those skilled in the art in understanding and implementing this disclosure, and do not impose any limitation on the scope of this disclosure. The disclosure described herein may be implemented in ways other than those described below.

[0018] In the following description and claims, unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure pertains.

[0019] References to "an embodiment," "embodiment," "exemplary embodiment," etc., in this disclosure indicate that the described embodiments may include specific features, structures, or characteristics, but not every embodiment needs to include specific features, structures, or characteristics. Furthermore, such phrases do not necessarily refer to the same embodiment. Moreover, when a specific feature, structure, or characteristic is described in connection with an exemplary embodiment, whether explicitly described or not, those skilled in the art will recognize that such a feature, structure, or characteristic affects its connection to other embodiments.

[0020] It should be understood that while the terms “first” and “second”, etc., may be used herein to describe various elements, these elements should not be limited by these terms. These terms are used only to distinguish one element from another. For example, without departing from the scope of the exemplary embodiments, a first element may be referred to as a second element, and similarly, a second element may be referred to as a first element. The term “and / or” as used herein includes any and all combinations of one or more of the listed terms.

[0021] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments. The singular forms “a,” “an,” and “the” used herein also include the plural forms unless the context clearly indicates otherwise. The terms “a group of elements” or “a collection of elements” as used herein are intended to include one or more elements. It should also be understood that the terms “comprising,” “including,” “having,” “possessing,” “including,” and / or “comprising,” when used herein, specify the presence of the stated features, elements, and / or components, but do not exclude the presence or addition of one or more other features, elements, components, and / or combinations thereof.

[0022] Figure 1 A flowchart of a satellite orbit control shutdown method provided in this application is shown. Figure 2 This application provides a logical diagram illustrating the orbit control execution process of a satellite.

[0023] refer to Figure 1 , Figure 2 This method is applied to satellites and includes: S10, determine the track control duration based on the track control data packet.

[0024] S20: Determine whether the track control duration is less than the track control duration threshold. If the track control duration is less than the track control duration threshold, proceed to step S30; otherwise, proceed to step S40.

[0025] S30 selects to control the satellite using the first strategy to perform the current orbit control task.

[0026] The first strategy includes the following steps S301-S303: S301, starting from the start time of the current track control task, record the start time.

[0027] The power-on duration refers to the operating time of the satellite's thrusters after they begin jetting. In other words, it is the duration of thruster jetting during orbit control operations.

[0028] In some embodiments, recording the power-on duration includes: From the moment the satellite receives the injection command, calculate the jet duration of the thruster in each control cycle corresponding to the current orbit control mission; The total jet duration is obtained by summing the jet durations within each control cycle. The jet duration of a single thruster is obtained as the start-up duration based on the total jet duration and the number of thrusters used.

[0029] Specifically, the satellite can query the usage status of the thrusters to determine whether the thrusters are used during orbit control execution. For thrusters that have been used, the jet duration in each control cycle is recorded by accumulating the commands. In this way, the total jet duration can be obtained by accumulating the jet duration in each control cycle. Dividing the total jet duration by the number of thrusters used can determine the jet duration of a single thruster, that is, the start-up time.

[0030] S302, determine whether the power-on duration is greater than or equal to the first duration threshold. If the power-on duration is greater than or equal to the first duration threshold, continue to step S303; otherwise, end the entire satellite autonomous control shutdown process and the satellite continues to perform the current orbit control task.

[0031] In some embodiments, the first duration threshold is 50 seconds. It should be understood that those skilled in the art can adjust the specific value of the first duration threshold according to actual needs, and there are no restrictions on this.

[0032] S303 generates a shutdown command to terminate the current track control task.

[0033] S40 selects to use the second strategy to control the satellite to perform the current orbit control task.

[0034] The second strategy includes the following steps S401-S405: S401, calculates the target velocity increment of the satellite.

[0035] Specifically, the target velocity increment can be calculated based on the measurement value of a single velocity increment measurement device (such as an accelerometer).

[0036] The velocity increment measurement unit can be a quartz accelerometer and / or an inertial accelerometer, specifically including the following situations: In some embodiments, the satellite is equipped with a quartz accelerometer to calculate the target velocity increment of the satellite, including: starting from the satellite receiving the uploading command, calculating the first velocity increment generated by the thruster in each control cycle corresponding to the current orbit control mission based on the first acceleration output data of the quartz accelerometer in the satellite's own system; and accumulating the calculated first velocity increments generated in each control cycle to obtain the target velocity increment of the satellite.

[0037] Among them, the uplink command can refer to the command sent by the ground station to the satellite to instruct the satellite to perform orbit control shutdown.

[0038] In other words, for a satellite equipped with a quartz accelerometer, after receiving the uploading command, the satellite enters the orbit control execution process. During this process, the satellite can calculate the first velocity increment generated in each control cycle based on the first acceleration output data measured by the quartz accelerometer. Then, the first velocity increments generated in each control cycle are accumulated to obtain the target velocity increment of the satellite.

[0039] In some embodiments, the satellite is equipped with an inertial measurement accelerometer to calculate the target velocity increment of the satellite, including: starting from the satellite receiving the uploading command, calculating the second velocity increment generated by the thruster in each control cycle corresponding to the current orbit control mission based on the second acceleration output data of the inertial measurement accelerometer in the X direction of the satellite's own system; and accumulating the calculated second velocity increments generated in each control cycle to obtain the target velocity increment of the satellite.

[0040] Among them, the uplink command can refer to the command sent by the ground station to the satellite to instruct the satellite to perform orbit control shutdown.

[0041] In other words, for a satellite equipped with an inertial accelerometer, after receiving the uploading command, the satellite enters the orbit control execution process. During this process, the satellite can calculate the second velocity increment generated in each control cycle based on the second acceleration output data measured by the inertial accelerometer. Then, the second velocity increments generated in each control cycle are accumulated to obtain the target velocity increment of the satellite.

[0042] In some embodiments, the satellite is equipped with a quartz accelerometer and an inertial measurement accelerometer to calculate the target velocity increment of the satellite, including: selecting one of the quartz accelerometer and the inertial measurement accelerometer as the target accelerometer based on accelerometer status information and / or priority information; using the target accelerometer to collect corresponding target acceleration output data; and calculating the target velocity increment of the satellite based on the target acceleration output data.

[0043] like Figure 2 As shown, for example, if the quartz accelerometer is determined to be usable based on its status information, but the inertial accelerometer is determined to be unusable based on its status information, the satellite selects the acceleration output data corresponding to the quartz accelerometer to calculate the target velocity increment; or, for example, if the quartz accelerometer has a higher priority than the inertial accelerometer, the satellite selects the acceleration output data corresponding to the quartz accelerometer to calculate the target velocity increment.

[0044] In some embodiments, after calculating the target velocity increment of the satellite, the method further includes: The effectiveness of the target velocity increment is judged based on the cross-verification mechanism of the quartz accelerometer and the inertial accelerometer. If the target velocity increment is deemed invalid, the control satellite continues to perform the current orbit control task.

[0045] The quartz accelerometer and the inertial accelerometer can use a cross-verification mechanism to determine the validity of the output data from both. When the cross-verification result is invalid (for example, the cross-verification flag is "2"), since the current target velocity increment cannot determine whether the satellite is currently powered off, the satellite ends the shutdown process and continues to perform the current orbit control task.

[0046] In some embodiments, the results of cross-validation can also be used as accelerometer status information to select a more suitable target accelerometer.

[0047] The advantage of this implementation is that, by introducing dual accelerometers to measure acceleration output data and setting corresponding priorities and introducing a cross-verification mechanism, the accuracy of the acceleration output data can be improved. Furthermore, because this scheme enhances the reliability of the satellite during orbit control execution, it can achieve high-precision and high-reliability complex orbit control for deep-space satellites with a low-cost, single-unit velocity increment configuration, offering a significant cost advantage.

[0048] S402, starting from the start time of the current track control task, record the start time.

[0049] S403, determine whether the target velocity increment is greater than or equal to the velocity increment threshold. If the target velocity increment is greater than or equal to the velocity increment threshold, proceed to step S404; otherwise, end the above shutdown procedure and the satellite continues to perform the current orbit control task.

[0050] S404, determine whether the power-on duration is greater than or equal to the second duration threshold. If the power-on duration is greater than or equal to the second duration threshold, proceed to step S405; otherwise, end the above shutdown procedure and the satellite continues to perform the current orbit control task.

[0051] In some embodiments, the second duration threshold is 80% multiplied by the track control duration.

[0052] It should be understood that those skilled in the art can also adjust the specific value of the first duration threshold according to actual needs, and there are no restrictions on this.

[0053] S405 generates a shutdown command to terminate the current track control task.

[0054] In summary, the satellite orbit control shutdown method, electronic equipment, storage medium, and program product provided in this application select either a first strategy or a second strategy to control the satellite to perform the current orbit control task by adjusting the orbit control duration. The first strategy determines whether to generate a shutdown command based on the power-on duration, while the second strategy determines whether to generate a shutdown command based on the power-on duration and the speed increment. In this way, a more suitable shutdown strategy can be selected for different orbit control tasks (such as short-term orbit control tasks and long-term orbit control tasks), improving the reliability of the shutdown command and thus ensuring orbit control safety and mission safety.

[0055] Figure 3 A schematic diagram of an electronic device provided in this application is shown. See also Figure 3 The electronic device includes one or more memories 301 and one or more processors 302, wherein the one or more memories 301 are coupled to and store instructions thereon, the instructions being executed individually or jointly by the one or more processors 302, causing the electronic device to perform the method as described in any of the first aspects.

[0056] It should be understood that the processor mentioned in the embodiments of this application can be a CPU, or other general-purpose processors, DSPs, ASICs, FPGAs, or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor can be a microprocessor or any conventional processor.

[0057] It should also be understood that the memory mentioned in the embodiments of this application can be volatile memory or non-volatile memory, or may include both volatile and non-volatile memory. Non-volatile memory can be read-only memory (ROM), programmable read-only memory, erasable programmable read-only memory, electrically erasable programmable read-only memory, or flash memory. Volatile memory can be random access memory (RAM), which is used as an external cache. By way of example, but not limitation, many forms of RAM are available, such as static random access memory, dynamic random access memory, synchronous dynamic random access memory, double data rate synchronous dynamic random access memory, enhanced synchronous dynamic random access memory, synchronous linked dynamic random access memory, and direct memory bus random access memory.

[0058] This application also provides a non-transitory computer-readable storage medium storing machine-executable instructions that can be executed by one or more processors of a machine. The machine may include electronic devices as mentioned above. When the machine-executable instructions are executed by one or more processors, the machine performs any of the methods mentioned above.

[0059] Computer-readable storage media may contain a propagated data signal containing computer program code, for example, on baseband or as part of a carrier wave. This propagated signal may take various forms, including electromagnetic, optical, and so on, or suitable combinations thereof. The computer-readable storage medium can be connected to an instruction execution system, apparatus, or device to enable communication, propagation, or transmission of a program for use. The program code located on the computer-readable storage medium can be propagated through any suitable medium, including radio, cable, fiber optic cable, radio frequency signals, or similar media, or any combination of the above media.

[0060] This disclosure also provides at least one computer program product tangibly stored on a non-transitory computer-readable storage medium. The computer program product includes computer-executable instructions, such as instructions included in a program module, which execute in a device on a target real or virtual processor to perform the aforementioned references. Figure 1 The method described herein. Typically, a program module includes routines, programs, libraries, objects, classes, components, data structures, etc., that perform specific tasks or implement specific abstract data types. In various embodiments, the functionality of a program module can be combined or separated among program modules as needed. The machine-executable instructions used in the program module can execute on a local or distributed device. In a distributed device, the program module can reside on both local and remote storage media.

[0061] Program code used to perform the methods of this disclosure may be written in any combination of one or more programming languages. This program code may be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing equipment such that, when executed by the processor or controller, the functions / operations specified in the flowcharts and / or block diagrams are implemented. The program code may be executed entirely on a machine, partially on a machine, partially on a remote machine, or entirely on a remote machine or server as a standalone software package.

[0062] In the context of this disclosure, computer program code or related data may be carried by any suitable carrier to enable a device, apparatus, or processor to perform the various processes and operations described above. Examples of carriers include signals, computer-readable media, etc.

[0063] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0064] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0065] To simplify the description of this application and thus aid in understanding one or more embodiments of the invention, the foregoing description of embodiments of this application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this disclosure method does not imply that the subject matter of this application requires more features than those mentioned in the claims. In fact, the embodiments contain fewer features than all the features of a single embodiment disclosed above.

[0066] In some embodiments, numbers describing the quantity of components and attributes are used. It should be understood that such numbers used in the description of embodiments are modified in some examples with the terms "approximately," "approximately," or "generally." Unless otherwise stated, "approximately," "approximately," or "generally" indicates that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may be changed depending on the characteristics required by individual embodiments. In some embodiments, numerical parameters should take into account specified significant digits and employ a general method of digit reservation. Although the numerical ranges and parameters used to confirm their breadth of scope in some embodiments of this application are approximate values, in specific embodiments, such values ​​are set as precisely as feasible.

[0067] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the essential spirit of this application will fall within the scope of the claims of this application.

Claims

1. A satellite orbit control shutdown method, characterized in that, include: The track control duration is determined based on the track control data packet, and it is determined whether the track control duration is less than the track control duration threshold. If the orbit control duration is less than the orbit control duration threshold, a first strategy is selected to control the satellite to perform the current orbit control task, wherein the first strategy includes: Starting from the moment the satellite receives the injection command, the jetting duration of the thruster in each control cycle corresponding to the current orbit control task is calculated. The jetting duration in each control cycle is accumulated to obtain the total jetting duration. Based on the total jetting duration and the number of thrusters used, the jetting duration of a single thruster is obtained as the start-up duration. If the power-on duration is greater than or equal to the first duration threshold, a power-off command is generated to terminate the current track control task; If the orbit control duration is greater than or equal to the orbit control duration threshold, a second strategy is selected to control the satellite to perform the current orbit control task, wherein the second strategy includes: Calculate the target velocity increment of the satellite; Record the startup duration starting from the startup time of the current track control task; If the target speed increment is greater than or equal to the speed increment threshold and the power-on duration is greater than or equal to the second duration threshold, a power-off command is generated to terminate the current track control task.

2. The method as described in claim 1, characterized in that, The satellite is equipped with a quartz accelerometer, and the calculation of the target velocity increment of the satellite includes: From the moment the satellite receives the injection command, the first velocity increment generated by the thruster in each control cycle corresponding to the current orbit control mission is calculated based on the first acceleration output data of the quartz accelerometer in the satellite's main system. The target velocity increment of the satellite is obtained by summing the first velocity increments generated in each control cycle.

3. The method as described in claim 1, characterized in that, The satellite is equipped with an inertial accelerometer, and the calculation of the target velocity increment of the satellite includes: From the moment the satellite receives the injection command, the second velocity increment generated by the thruster in each control cycle corresponding to the current orbit control mission is calculated based on the second acceleration output data of the inertial accelerometer in the X direction of the satellite's own system. The target velocity increment of the satellite is obtained by summing the second velocity increments generated in each control cycle.

4. The method as described in claim 1, characterized in that, The satellite is equipped with a quartz accelerometer and an inertial measurement unit (IMU). The calculation of the target velocity increment of the satellite includes: Based on the accelerometer status information and / or priority information, select one of the quartz accelerometer and the inertial measurement accelerometer as the target accelerometer; The target accelerometer is used to collect the corresponding target acceleration output data, and the target velocity increment of the satellite is calculated based on the target acceleration output data.

5. The method as described in claim 4, characterized in that, After calculating the target velocity increment of the satellite, the method further includes: The effectiveness of the target velocity increment is determined based on the cross-verification mechanism between the quartz accelerometer and the inertial accelerometer. If the target velocity increment is determined to be invalid, the satellite is controlled to continue performing the current orbit control task.

6. The method according to any one of claims 1-5, characterized in that, The first duration threshold is 50 seconds; the second duration threshold is 80% multiplied by the track control duration.

7. An electronic device, comprising: One or more processors; as well as One or more memories coupled to the one or more processors and storing instructions thereon, which, when executed individually or jointly by the one or more processors, cause the electronic device to perform the method according to any one of claims 1-6.

8. A non-transitory computer-readable storage medium storing machine-executable instructions, which, when executed by one or more processors of the machine, cause the machine to perform the method of any one of claims 1-6.

9. A computer program product comprising machine-executable instructions, which, when executed by one or more processors of a machine, cause the machine to perform the method of any one of claims 1-6.

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