Spacecraft orbit determination method and device, electronic equipment and storage medium

Abstract

The invention provides a spacecraft orbit determination method and device, electronic equipment and a storage medium, and relates to the technical field of spacecraft engineering. The spacecraft orbit determination method comprises the following steps: acquiring orbit determination measurement data in response to a target triggering operation; wherein the target triggering operation is used for triggering an orbit determination task of a spacecraft to be subjected to orbit determination; determining an initial orbit determination result of the spacecraft to be subjected to orbit determination based on the orbit determination measurement data, and auditing the initial orbit determination result based on a preset auditing rule; and determining the orbit of the spacecraft to be subjected to orbit determination based on the audit result. According to the method, the orbit determination task of the spacecraft is triggered through the target triggering operation, so that automatic operation of spacecraft orbit determination is realized, and the cost is reduced; besides, according to the embodiment of the invention, the initial orbit determination result of the spacecraft is audited through the preset auditing rule, and the spacecraft orbit is determined based on the auditing result, so that the accuracy of orbit determination is improved.

Description

Technical Field

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

[0002] Spacecraft orbit determination refers to the process of using measurement data to determine the orbit of a spacecraft in space. Spacecraft orbit determination is of great significance to the safe and efficient operation of spacecraft. With the development of the aerospace industry, the number of spacecraft in orbit is increasing, and the corresponding on-orbit management work is also increasing day by day, especially the work related to orbit determination calculations has become more cumbersome and complicated.

[0003] The existing methods for determining spacecraft orbits have high requirements on the professional capabilities of spacecraft managers, and the degree of automation of business process control and the accuracy of orbit determination are relatively low. Summary of the invention

[0004] In view of this, the embodiments of the present disclosure propose a method, device, electronic device and storage medium for determining a spacecraft orbit, so as to solve the problems existing in the related technologies, such as high requirements for the professional capabilities of spacecraft managers, low degree of automation of business process control and low accuracy of orbit determination.

[0005] According to a first aspect of the present disclosure, a method for determining a spacecraft orbit is provided, comprising: acquiring orbit determination measurement data in response to a target trigger operation; wherein the target trigger operation is used to trigger an orbit determination task for a spacecraft to be orbit determined; determining an initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and reviewing the initial orbit determination result based on preset review rules; and determining the orbit of the spacecraft to be orbit determined based on the review result.

[0006] According to a second aspect of the present disclosure, a spacecraft orbit determination device is provided, comprising: a trigger module, configured to obtain orbit determination measurement data in response to a target trigger operation; wherein the target trigger operation is configured to trigger an orbit determination task for a spacecraft to be orbit determined; an audit module, configured to determine an initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and to audit the initial orbit determination result based on preset audit rules; and a determination module, configured to determine the orbit of the spacecraft to be orbit determined based on the audit result.

[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 which, when executed by the processor, cause the processor to execute the above-mentioned spacecraft orbit determination 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 orbit determination method.

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

[0010] In the spacecraft orbit determination method provided in the example implementation mode of the present disclosure, orbit determination measurement data is obtained in response to a target trigger operation; wherein the target trigger operation is used to trigger the orbit determination task of the spacecraft to be orbit determined; an initial orbit determination result of the spacecraft to be orbit determined is determined based on the orbit determination measurement data, and the initial orbit determination result is reviewed based on preset review rules; and the orbit of the spacecraft to be orbit determined is determined based on the review result. The embodiment of the present disclosure triggers the orbit determination task of the spacecraft through the target trigger operation, realizes the automated operation of the spacecraft orbit determination, greatly reduces the workload of conventional orbit determination of spacecraft managers, improves efficiency, and reduces costs; in addition, the embodiment of the present disclosure reviews the initial orbit determination result of the spacecraft through preset review rules, and determines the spacecraft orbit based on the review result, thereby improving the accuracy of the orbit determination.

[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 method for determining a spacecraft orbit according to an exemplary embodiment of the present disclosure is shown;

[0014] Figure 2 A functional structural diagram of a spacecraft orbit determination system according to an exemplary embodiment of the present disclosure is shown;

[0015] Figure 3 A flow chart showing another method for determining a spacecraft orbit according to an exemplary embodiment of the present disclosure is shown;

[0016] Figure 4 A flow chart showing an automated operation process of orbit determination in another method for determining a spacecraft orbit according to an exemplary embodiment of the present disclosure is shown;

[0017] Figure 5 A schematic block diagram of a spacecraft orbit determination device according to an exemplary embodiment of the present disclosure is shown;

[0018] Figure 6A structural block diagram of an exemplary electronic device that can be used to implement the embodiments of the present disclosure is shown. DETAILED DESCRIPTION

[0019] 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.

[0020] 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.

[0021] 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.

[0022] 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".

[0023] 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.

[0024] The embodiments of the present disclosure provide a method, device, electronic device and storage medium for determining a spacecraft orbit. The embodiments of the present disclosure are described below with reference to the accompanying drawings.

[0025] The present disclosure first provides a method for determining a spacecraft orbit. Figure 1 As shown, the spacecraft orbit determination method specifically includes the following steps:

[0026] S110: In response to a target triggering operation, obtaining orbit determination measurement data; wherein the target triggering operation is used to trigger an orbit determination task of the spacecraft to be orbit determined;

[0027] S120: determining an initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and reviewing the initial orbit determination result based on a preset review rule;

[0028] S130: Determine the orbit of the spacecraft to be orbit-determined based on the review result.

[0029] The spacecraft orbit determination method provided in the embodiment of the present disclosure triggers the orbit determination task of the spacecraft through a target trigger operation, thereby realizing the automated operation of the spacecraft orbit determination, greatly reducing the workload of conventional orbit determination of spacecraft management personnel, improving efficiency and reducing costs; in addition, the embodiment of the present disclosure audits the initial orbit determination results of the spacecraft through preset audit rules, and determines the spacecraft orbit based on the audit results, thereby improving the accuracy of the orbit determination.

[0030] Next, in another embodiment, the above steps are described in more detail.

[0031] In step S110, in response to a target triggering operation, orbit determination measurement data is acquired; wherein the target triggering operation is used to trigger an orbit determination task of the spacecraft to be orbit determined.

[0032] 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. The above-mentioned spacecraft to be determined is a spacecraft whose orbit needs to be determined according to the spacecraft orbit determination method provided in the embodiments of the present application. For example, the above-mentioned spacecraft can be a spacecraft such as a satellite, a probe, or a rocket.

[0033] In an embodiment of the present application, the orbit determination measurement data is used to determine the orbit of the spacecraft to be orbit determined. Exemplarily, the orbit determination measurement data may include Global Navigation Satellite System (GNSS) data, where GNSS data refers to signal data received through the Global Navigation Satellite System.

[0034] In the embodiment of the present application, the above-mentioned orbit determination task refers to the task of determining the orbit of the above-mentioned spacecraft to be orbit determined by an orbit determination algorithm based on the above-mentioned orbit determination measurement data.

[0035] In an embodiment of the present application, the target triggering operation is used to trigger the track determination task.

[0036] In the embodiment of the present application, the above target trigger operation can be that the current time reaches a preset task trigger time, that is, the orbit determination task is triggered by setting the task trigger time. Exemplarily, the process of triggering the orbit determination task by preset time can be implemented as follows: setting the task trigger time of the orbit determination task; when it is detected that the current time reaches the task trigger time, obtaining orbit determination measurement data.

[0037] In the embodiment of the present application, the task trigger time is a trigger time set based on the determination requirements of the spacecraft orbit. For example, if it is determined based on the daily orbit determination requirements of the spacecraft that the spacecraft orbit needs to be determined twice a day, the task trigger time can be set to 8 am and 6 pm, and the scheduled orbit determination task can be added based on this task trigger time, so that the system automatically starts the orbit determination task and runs it at 8 am and 6 pm every day.

[0038] In the embodiment of the present application, the orbit determination task can be automatically executed through the target trigger operation, which greatly reduces the conventional orbit determination workload of spacecraft managers and reduces labor costs.

[0039] In an embodiment of the present application, the above-mentioned acquisition of orbit determination measurement data can, exemplarily, be implemented as follows: acquiring raw orbit determination measurement data; wherein the raw orbit determination measurement data includes global satellite navigation system data; performing data processing on the raw orbit determination measurement data based on preset data processing rules to obtain the orbit determination measurement data.

[0040] In the embodiment of the present application, the above-mentioned preset data processing rules are used to process the acquired orbit determination measurement raw data to achieve the purpose of constraining the data quality of the orbit determination measurement data. Exemplarily, the data processing process may include data deduplication, sorting, splitting, and removing outliers.

[0041] In an embodiment of the present application, the above-mentioned preset data processing rules can be set based on experience. Exemplarily, the preset data processing rules may include the following: (1) GNSS data is used for orbit determination first. Exemplarily, the GNSS data received by the tracking and control station within 12 hours before the mission trigger time can be used; (2) It is necessary to ensure that the orbit determination calculation orbit measurement data is not less than 50; (3) The orbit measurement data are not repeated and are arranged in chronological order; (4) To ensure data continuity, the time interval of each orbit measurement data shall not exceed 5 minutes; (5) The distance between each point of data and the center of the earth is calculated, and if it exceeds the threshold, the wild value is eliminated. It should be noted that the above-mentioned preset data processing rules are only exemplary, and the protection scope of the embodiment of the present application is not limited to this. For example, the above-mentioned preset data processing rules may also be other rules set based on the actual situation of the spacecraft to be orbit determined and expert experience.

[0042] In step S120, an initial orbit determination result of the spacecraft to be orbit determined is determined based on the orbit determination measurement data, and the initial orbit determination result is reviewed based on preset review rules.

[0043] In the embodiment of the present application, the above-mentioned initial orbit determination result is the orbital parameters of the spacecraft obtained by running the orbit determination algorithm for the first time based on the above-mentioned orbit determination measurement data, which is used to characterize the shape, position and motion characteristics of the orbit. Specifically, the above-mentioned orbital parameters may include semi-major axis, eccentricity, orbital inclination, periapsis angle, ascending node longitude, and true anomaly angle.

[0044] In an embodiment of the present application, the above-mentioned orbit determination algorithm is used to determine the orbital parameters of the spacecraft. Specifically, the orbit determination algorithm may include data preprocessing, initial orbit determination and orbit improvement steps. Among them, the above-mentioned data preprocessing step includes: using measuring instruments to track and observe the spacecraft to obtain a large amount of position information and velocity information; the above-mentioned initial orbit determination step includes: using observation data to estimate the orbital elements, that is, the six elements of the orbit (semi-major axis, eccentricity, orbital inclination, pericentric angle, ascending node longitude, true anomaly); the above-mentioned orbit improvement step includes: using a large amount of observation data to correct the initial orbit to obtain accurate orbital elements.

[0045] In the embodiment of the present application, the above-mentioned preset audit rules are used to control the correctness of the current orbit determination result, which can be determined based on actual needs and experience. If the audit is passed, the current orbit determination result is used as the final orbit determination result of the spacecraft. If the audit fails, the recalculation process is entered. Among them, the recalculation process refers to the process of re-executing the orbit determination algorithm to obtain orbit parameters.

[0046] Exemplarily, the above-mentioned preset review rules may include: (1) the utilization rate of orbit determination measurement data is not less than 95%; (2) the RMS value of the orbit determination algorithm calculation error is less than 0.0000001; (3) the position error between the improved orbit and the last confirmed improved orbit must be kept within a certain range, and when extrapolated to the same time point under a stable space environment (refer to the daily F10.7 and geomagnetic index, the smaller the value, the more stable), it shall not exceed 2 kilometers within a 10-hour range, and shall not exceed 5 kilometers when the space environment is severely disturbed; (4) compared with the orbit height of the orbit determination result at the same time of the previous day, the descent height shall not exceed 170 meters.

[0047] Furthermore, the above-mentioned audit of the initial orbit determination result based on the preset audit rules can be implemented as follows: determine whether the target parameters of the initial orbit determination result meet the preset audit rules, and obtain the audit results; wherein the target parameters of the initial orbit determination result include the data utilization rate, internal conformity accuracy, spatial position error and orbit height change of the orbit measurement data. That is, in combination with the above-mentioned preset audit rules, the indicators such as data utilization rate, internal conformity accuracy, spatial position error, orbit height change, etc. are evaluated in turn.

[0048] In step S130, the orbit of the spacecraft to be orbit-determined is determined based on the review result.

[0049] In an embodiment of the present application, after the initial orbit determination result is reviewed based on the above-mentioned preset review rules, the orbit of the spacecraft to be determined can be further determined based on the review results. Exemplarily, the implementation process of determining the orbit of the spacecraft to be determined based on the review results can be as follows: if the review result is passed, the orbit of the spacecraft to be determined is determined based on the initial orbit determination result; if the review result is failed, the orbit of the spacecraft to be determined is re-determined based on the preset recalculation rules. That is, after evaluating the data utilization rate, internal conformity accuracy, spatial position error, orbit height change and other indicators in turn in combination with the above-mentioned preset review rules, if all evaluation indicators are met, the orbit determination result is automatically confirmed, and the improved orbit determination result is published at the same time, providing the latest satellite orbit information for downstream businesses.

[0050] In the embodiment of the present application, the above-mentioned preset recalculation rules are used to guide the adjustment of orbit determination recalculation parameters, that is, to guide the adjustment of orbit determination measurement data in the above-mentioned recalculation process.

[0051] Exemplarily, the preset recalculation rules may include: (1) adjusting the time range of orbit determination measurement data, and using the real-time telemetry data received from the most recent two tracking laps to initiate orbit determination calculations; (2) adjusting the data weight distribution of orbit determination measurement data, and adjusting the weight of position data to be higher than that of velocity data; (3) adjusting the allowable error of orbit determination measurement data to improve the utilization rate of orbit determination measurement data.

[0052] Furthermore, re-determining the orbit of the spacecraft to be orbit determined based on the preset recalculation rules can be achieved as follows: judging whether the current number of recalculation times exceeds the preset recalculation threshold; if the current number of recalculation times does not exceed the preset recalculation threshold, adjusting the target parameters of the orbit determination measurement data based on the preset recalculation rules; wherein the target parameters of the orbit determination measurement data include the time range of the orbit determination measurement data, the data weight distribution and the measurement error; and re-determining the orbit of the spacecraft to be orbit determined based on the adjusted orbit determination measurement data.

[0053] Specifically, assuming that the above-mentioned preset recalculation threshold is set to 3 times, when the initial orbit determination result fails to pass the review, the orbit determination measurement data is adjusted according to the above-mentioned preset recalculation rule, and the above-mentioned orbit determination algorithm is executed based on the adjusted orbit determination measurement data to obtain new orbit parameters as the current orbit determination result; the current orbit determination result is reviewed based on the above-mentioned preset review rules. If it passes the review, the current orbit determination result is used as the final orbit determination result of the spacecraft, and the orbit determination result is automatically confirmed. At the same time, the improved orbit determination result is published to provide the latest satellite orbit information for downstream businesses; if it fails the review, the above process is continued until the current orbit determination result passes the review or the number of recalculations reaches 3 times.

[0054] In an embodiment of the present application, if the current number of recalculation times exceeds a preset recalculation threshold, the spacecraft orbit method provided in the embodiment of the present application can also send an alarm message to notify the spacecraft management personnel to complete the orbit determination operation through manual intervention.

[0055] The spacecraft orbit determination method provided in the embodiment of the present disclosure triggers the orbit determination task of the spacecraft through a target trigger operation, thereby realizing the automated operation of the spacecraft orbit determination, greatly reducing the workload of conventional orbit determination of spacecraft management personnel, improving efficiency and reducing costs; in addition, the embodiment of the present disclosure audits the initial orbit determination results of the spacecraft through preset audit rules, and determines the spacecraft orbit based on the audit results, thereby improving the accuracy of the orbit determination.

[0056] Below, in a specific embodiment, taking the implementation of orbit determination automation operation for a single satellite with an orbit altitude of 500 kilometers as an example, the overall process of the spacecraft orbit determination method of the embodiment of the present application is described:

[0057] The spacecraft orbit determination method provided in the embodiment of the present application can be based on Figure 2 The spacecraft orbit determination system shown is implemented as follows, Figure 2 The functional block diagram of the spacecraft orbit determination system. Figure 2 As shown, the spacecraft orbit determination system includes a basic configuration module, a task scheduling module, an orbit determination calculation module, a result review module, an orbit determination recalculation module and a monitoring and display module. Among them:

[0058] The above basic configuration module is used to configure the spacecraft, tracking and control station, space perturbation and expert experience;

[0059] The above-mentioned task scheduling module is used to implement workflow configuration, rule-based automated task execution, message-driven and task status update;

[0060] The orbit determination calculation module is used to perform measurement data loading, measurement data processing, orbit determination calculation and orbit extrapolation calculation;

[0061] The above result review module is used to implement measurement data usage rate inspection, spatial position change comparison, control forecast result hyperloop review, and control parameter safety review;

[0062] The orbit determination recalculation module is used to perform measurement data adjustment, perturbation parameter adjustment, data weight adjustment and measurement operation error adjustment;

[0063] The above-mentioned monitoring and display module is used to realize the display of calculation records, success and failure status, data usage, improvement results, internal compliance accuracy and track improvement.

[0064] Relying on the functions of the above modules, the above spacecraft orbit determination method, such as Figure 3 As shown, the specific steps include:

[0065] Step S310: Configure satellite information.

[0066] In this step, the satellite mass, satellite atmospheric drag area, solar light pressure area, satellite current orbit and other information are configured through the above-mentioned basic configuration module.

[0067] Step S320: configuring spatial perturbation environment parameters.

[0068] In this step, the space perturbation environment parameters are configured through the above-mentioned basic configuration module, including the atmospheric damping coefficient, solar light pressure coefficient, solar radiation index, geomagnetic index, etc., among which the solar radiation index and geomagnetic index can obtain the latest data provided by the authoritative organization in real time through the network interface.

[0069] Step S330: Determine the automated operation process of the track determination task.

[0070] In this step, the automated operation process of the spacecraft orbit determination task is formulated according to the orbit determination business through the task scheduling module. Exemplarily, the automated operation process of the spacecraft orbit determination task can be based on the Activiti open source business process management platform.

[0071] Step S340: configuring the expert experience knowledge base.

[0072] In this step, the expert experience knowledge base configuration for the automated operation of spacecraft orbit determination is added through the above basic configuration module, wherein the above expert experience knowledge base configuration includes configurations of expert experience for preprocessing measurement data, expert experience for reviewing orbit determination results, and expert experience for adjusting orbit determination recalculation parameters. Specifically:

[0073] The above data preprocessing expert experience is mainly used to constrain the quality of measurement data, including:

[0074] (1) Prioritize the use of GNSS data for orbit determination;

[0075] (2) It is necessary to ensure that the calculated measurement data for orbit determination is no less than 50;

[0076] (3) The measurement data must not be repeated and must be arranged in chronological order;

[0077] (4) To ensure data continuity, the time interval between each piece of data shall not exceed 5 minutes;

[0078] (5) Calculate the distance between each data point and the center of the earth, and remove outliers if they exceed the threshold.

[0079] The above orbit determination result review expert experience is used to control the correctness of the orbit determination results, including:

[0080] (1) The utilization rate of measurement data is not less than 95%;

[0081] (2) The orbit determination calculation error meets the accuracy RMS value less than 0.0000001;

[0082] (3) The position error between the improved orbit and the last confirmed improved orbit must be kept within a certain range. When extrapolated to the same time point under a stable space environment (refer to the daily F10.7 and geomagnetic index, the smaller the value, the more stable), it should not exceed 2 kilometers within a 10-hour period; and should not exceed 5 kilometers under severe space environment disturbances.

[0083] (4) Compared with the orbit height determined at the same time on the previous day, the decrease in height does not exceed 170 meters.

[0084] The above expert experience in orbit determination recalculation parameter adjustment is used to guide orbit determination recalculation parameter adjustment, including:

[0085] (1) Adjust the measurement data and initiate orbit determination calculations using the real-time telemetry data received during the last two tracking laps;

[0086] (2) Adjust the weight of the measurement data, so that the weight of the position data is higher than that of the velocity data;

[0087] (3) Adjust the allowable error of measurement data and improve the utilization rate of measurement data for track determination.

[0088] Step S350: Configure the satellite daily orbit determination requirements.

[0089] In this step, the daily orbit determination requirements of the satellite are configured through the above-mentioned task scheduling module. For example, two orbit determinations are required every day, at 8:00 in the morning and 18:00 in the evening. The orbit determination measurement data uses the GNSS data received by the tracking and control station within 12 hours before the orbit determination calculation. Based on this condition, a timed orbit determination task is added to the task scheduling module. Exemplarily, the trigger time of the above-mentioned configuration of the spacecraft orbit determination task can be implemented based on the xxl-job distributed centralized scheduling platform.

[0090] Step S360: When the triggering condition is met, the track determination automation process is automatically started, and the track determination operation is completed under the drive of the workflow.

[0091] In this step, taking the above-mentioned added scheduled orbit determination task as an example, at 8:00 and 18:00 every day, the spacecraft orbit determination system will automatically start the orbit determination automation operation process determined in the above step S330, and complete the orbit determination operation driven by the workflow.

[0092] Specifically, the above-mentioned automatic start of the track determination automation operation process completes the track determination operation process driven by the workflow, such as Figure 4 As shown, this can be achieved through the following steps:

[0093] Step S401: Automatic scheduling triggering.

[0094] Step S402: Loading measurement data for orbit determination.

[0095] In this step, the measurement data for orbit determination is loaded through the orbit determination calculation module, specifically, the GNSS data within 12 hours before the trigger time specified by the timing orbit determination task is loaded.

[0096] Step S403: pre-process the measurement data.

[0097] In this step, the measurement data loaded in step S402 is preprocessed by the track determination calculation module based on the data preprocessing expert experience, such as deduplication, sorting, splitting, and outlier removal.

[0098] Step S404: Execute orbit determination operation.

[0099] In this step, the orbit determination calculation module reads measurement data, space perturbation information, satellite quality and other information through the orbit determination core algorithm, completes the orbit determination calculation based on the above information read, and outputs the calculation result.

[0100] Step S405: Review the track determination result.

[0101] In this step, the above-mentioned result review module is used to review and evaluate indicators such as data utilization rate, internal accuracy, spatial position error, and orbit height change based on the above-mentioned orbit determination result review expert experience.

[0102] Step S406: Determine whether the track determination result is correct.

[0103] In this step, it is determined whether the track determination result is correct based on the audit evaluation result of step S405. Specifically, if the track determination result meets all evaluation indicators, the track determination result is automatically confirmed and step S407 is continued; if the audit fails, step S408 is continued.

[0104] Step S407: Publish the track determination result.

[0105] In this step, the orbit determination result is published through the above-mentioned monitoring and display module to provide the latest satellite orbit information for downstream businesses.

[0106] Step S408: Determine whether the maximum number of recalculation times has been exceeded.

[0107] In this step, if it is determined that the maximum number of recalculations has not been exceeded, step S409 is continued; if the maximum number of recalculations has been exceeded, step S410 is continued. The maximum number of recalculations is a preset threshold, for example, the maximum number of recalculations can be set to 3 times, and when the orbit recalculation fails more than 3 times, step S410 is continued.

[0108] Step S409: Adjust the measurement data.

[0109] In this step, the orbit determination recalculation module adjusts the measurement data time range, position and velocity data weight, and measurement error configuration in sequence based on the orbit determination recalculation parameter adjustment expert experience. Specifically, the measurement data loading process of step S402 can be guided based on the orbit determination recalculation parameter adjustment expert experience, and the process jumps to step S403 to re-initiate orbit determination calculation.

[0110] Step S410: Send warning information.

[0111] In this step, when the orbit recalculation fails more than three times, an abnormal notification is initiated through the above-mentioned monitoring and display module to inform the satellite management personnel to complete the orbit determination operation by manual intervention.

[0112] For example, the above-mentioned spacecraft orbit determination system can also provide information display functions such as orbit determination record display, orbit determination task status display, orbit determination result display, orbit determination space position change display, etc. through the above-mentioned monitoring display module. Through a good human-computer interaction interface, managers can reduce their workload while also being able to more clearly and accurately grasp the real-time status information of satellite orbit determination.

[0113] The above spacecraft orbit determination method has the following advantages:

[0114] (1) The orbit determination was automated by developing an automated process and expert database, which greatly reduced the workload of satellite managers for routine orbit determination.

[0115] (2) Based on the configured expert database, the automated operation judgment rules can be customized for different satellites;

[0116] (3) Detailed track determination records and track determination result displays enable managers to clearly understand track changes;

[0117] (4) Rely on the system timing drive and real-time alarm mechanism to proactively notify management personnel to avoid omissions in satellite orbit determination work.

[0118] 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.

[0119] The embodiment of the present invention can divide the functional modules of the spacecraft orbit determination 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.

[0120] Accordingly, the embodiment of the present disclosure also provides a spacecraft orbit determination device. Figure 5As shown, the spacecraft orbit determination device 500 may include a trigger module 510, a review module 520 and a determination module 530, wherein:

[0121] The trigger module 510 may be used to obtain orbit determination measurement data in response to a target trigger operation; wherein the target trigger operation is used to trigger an orbit determination task of the spacecraft to be orbit determined;

[0122] The review module 520 may be used to determine the initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and review the initial orbit determination result based on preset review rules;

[0123] The determination module 530 may be used to determine the orbit of the spacecraft to be orbit determined based on the review result.

[0124] In the embodiment of the present application, the trigger module is specifically used to: set the task trigger time of the orbit determination task; and obtain orbit determination measurement data when it is detected that the current time reaches the task trigger time.

[0125] In an embodiment of the present application, the above-mentioned trigger module is specifically used to: obtain orbit determination measurement raw data; wherein the orbit determination measurement raw data includes global satellite navigation system data; and perform data processing on the orbit determination measurement raw data based on preset data processing rules to obtain orbit determination measurement data.

[0126] In an embodiment of the present application, the above-mentioned audit module is specifically used to: determine whether the target parameters of the initial orbit determination result meet the preset audit rules to obtain the audit result; wherein, the target parameters of the initial orbit determination result include the data utilization rate, internal conformity accuracy, spatial position error and orbit height change of the orbit determination measurement data.

[0127] In an embodiment of the present application, the above-mentioned determination module is specifically used to: if the audit result is passed, determine the orbit of the spacecraft to be orbit determined based on the initial orbit determination result; if the audit result is failed, re-determine the orbit of the spacecraft to be orbit determined based on a preset recalculation rule.

[0128] In an embodiment of the present application, the above-mentioned determination module is specifically used to: determine whether the current number of recalculation times exceeds a preset recalculation threshold; if the current number of recalculation times does not exceed the preset recalculation threshold, adjust the target parameters of the orbit determination measurement data based on the preset recalculation rules; wherein the target parameters of the orbit determination measurement data include the time range of the orbit determination measurement data, the data weight distribution and the measurement error; and re-determine the orbit of the spacecraft to be orbit determined based on the adjusted orbit determination measurement data.

[0129] In an embodiment of the present application, the above-mentioned spacecraft orbit determination device also includes an alarm module, which is specifically used to: if the current number of recalculation times exceeds a preset recalculation threshold, send an alarm message to the spacecraft management personnel to notify the spacecraft management personnel to determine the orbit of the spacecraft to be determined by manual intervention.

[0130] In addition, the specific implementation details of the above-mentioned spacecraft orbit determination device have been described in detail in the corresponding position of the spacecraft orbit determination method, so they will not be repeated here.

[0131] Figure 6 Schematic diagram of the structure of an electronic device in the embodiment of the present disclosure. Figure 6 , which shows a structural schematic diagram of an electronic device 600 suitable for implementing the embodiments of the present disclosure. Figure 6 The 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.

[0132] like Figure 6 As shown, the electronic device 600 may include a processing device (e.g., a central processing unit, a graphics processing unit, etc.) 601, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 602 or a program loaded from a storage device 608 to a random access memory (RAM) 603 to implement the spacecraft orbit determination method of the embodiment described in the present disclosure. Various programs and data required for the operation of the electronic device 600 are also stored in the RAM 603. The processing device 601, the ROM 602, and the RAM 603 are connected to each other via a bus 604. An input / output (I / O) interface 605 is also connected to the bus 604.

[0133] Typically, the following devices may be connected to the I / O interface 605: an input device 606 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 607 including, for example, a liquid crystal display (LCD), a speaker, a vibrator, etc.; a storage device 608 including, for example, a magnetic tape, a hard disk, etc.; and a communication device 609. The communication device 609 may allow the electronic device 600 to communicate with other devices wirelessly or by wire to exchange data. Although Figure 6 The electronic device 600 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.

[0134] 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 a program code for executing the method shown in the flowchart, thereby implementing the spacecraft orbit determination method as described above. In such an embodiment, the computer program can be downloaded and installed from the network through the communication device 609, or installed from the storage device 608, or installed from the ROM 602. When the computer program is executed by the processing device 601, the above functions defined in the method of the embodiment of the present disclosure are executed.

[0135] 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.

[0136] 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.

[0137] The computer-readable medium may be included in the electronic device, or may exist independently without being incorporated into the electronic device.

[0138] The computer-readable medium carries one or more programs. When the one or more programs are executed by the electronic device, the electronic device:

[0139] In response to a target trigger operation, orbit determination measurement data is acquired; wherein the target trigger operation is used to trigger an orbit determination task of the spacecraft to be orbit determined;

[0140] Determine the initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and review the initial orbit determination result based on the preset review rules;

[0141] The orbit of the spacecraft to be orbited is determined based on the review results.

[0142] 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.

[0143] 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).

[0144] 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.

[0145] 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, limit the unit itself.

[0146] 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.

[0147] 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.

[0148] 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.

[0149] 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.

[0150] 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 method for determining a spacecraft orbit, characterized in that: include: In response to a target triggering operation, orbit determination measurement data is acquired; wherein the target triggering operation is used to trigger an orbit determination task of the spacecraft to be orbit determined; Determining an initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and reviewing the initial orbit determination result based on a preset review rule; The orbit of the spacecraft to be orbit-determined is determined based on the review result.

2. The method for determining a spacecraft orbit according to claim 1, characterized in that: The step of acquiring orbit determination measurement data in response to the target triggering operation includes: Setting a task trigger time for the track determination task; When it is detected that the current time reaches the task triggering time, the orbit determination measurement data is acquired.

3. The method for determining a spacecraft orbit according to claim 2, characterized in that: The obtaining of the orbit determination measurement data comprises: Acquiring original orbit determination measurement data; wherein the original orbit determination measurement data includes global satellite navigation system data; The orbit determination measurement raw data is processed based on preset data processing rules to obtain the orbit determination measurement data.

4. The method for determining a spacecraft orbit according to claim 1, characterized in that: The reviewing of the initial orbit determination result based on the preset review rules includes: Determine whether the target parameters of the initial orbit determination result meet the preset audit rules to obtain an audit result; wherein the target parameters of the initial orbit determination result include the data utilization rate, internal coincidence accuracy, spatial position error and orbit height change of the orbit determination measurement data.

5. The method for determining a spacecraft orbit according to claim 1, characterized in that: Determining the orbit of the spacecraft to be orbit-determined based on the review result includes: If the audit result is passed, determining the orbit of the spacecraft to be orbit determined based on the initial orbit determination result; If the audit result is failure, the orbit of the spacecraft to be determined is re-determined based on a preset recalculation rule.

6. The method for determining the spacecraft orbit according to claim 5, characterized in that: The re-determining the orbit of the spacecraft to be orbit determined based on a preset recalculation rule comprises: Determine whether the current number of recalculation times exceeds the preset recalculation threshold; If the current number of recalculation times does not exceed the preset recalculation threshold, adjusting the target parameters of the orbit determination measurement data based on the preset recalculation rule; wherein the target parameters of the orbit determination measurement data include the time range, data weight distribution and measurement error of the orbit determination measurement data; The orbit of the spacecraft to be orbit determined is re-determined based on the adjusted orbit determination measurement data.

7. The method for determining a spacecraft orbit according to claim 6, characterized in that: The method further comprises: If the current number of recalculation times exceeds the preset recalculation threshold, an alarm message is sent.

8. A spacecraft orbit determination device, characterized in that: include: A trigger module, configured to obtain orbit determination measurement data in response to a target trigger operation; wherein the target trigger operation is used to trigger an orbit determination task of the spacecraft to be orbit determined; An audit module, configured to determine an initial orbit determination result of the spacecraft to be orbit determined based on the orbit determination measurement data, and audit the initial orbit determination result based on a preset audit rule; A determination module is used to determine the orbit of the spacecraft to be orbit determined based on the review result.

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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