Satellite situation information rapid generation method

Abstract

The invention discloses a satellite situation information rapid generation method, and solves the problem of how to improve the generation efficiency and accuracy of satellite situation information. Belongs to the field of satellite situation information generation. Comprising the following steps: embedding an STKX component in an STK into a GUI (Graphical User Interface) of a QT third-party software interface in a form of an ActiveX control; setting a target parameter in the QT third-party software interface in a mode of modifying the configuration file; based on a TCP protocol, QT third-party software is used as a client, a target parameter obtaining request is sent to the server, and target satellite orbit data corresponding to target parameters in the satellite orbit database are received; the QT third-party software creates an STK scene through an ExecuteCommand () function provided by the STKX component, target satellite orbit data specified in the target parameters are added into the STK scene to be displayed, data in a report is generated and summarized to obtain situation information of all satellites, and rapid generation of the satellite situation information is achieved; according to the method, the multi-satellite situation information is quickly and accurately generated, and the situation information generation efficiency is greatly improved.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite situation information generation, and in particular relates to a method for quickly generating satellite situation information. Background Art

[0002] Satellite situation information mainly includes data such as satellite orbit altitude, drift rate, inclination, sub-satellite point longitude, and rendezvous information with other satellites. The Satellite Tool Kit (STK) is widely used to generate satellite situation information.

[0003] At present, there are usually two ways to generate satellite situation information using STK software: one is to manually operate STK software to generate, by manually setting STK scene properties and satellite properties to create scenes and add satellites, and after generating various reports, manually filter out the required data, and obtain satellite situation information after analysis and processing; the other is to write third-party application software to automatically call STK software to generate, mostly using Matlab software, using STK / Connect module to realize the interconnection between Matlab software and STK software, so that third-party application software can send commands to STK software and receive data returned by STK software, that is, use third-party application software instead of manual operation of STK software to automatically complete a series of operations such as scene creation, adding satellites, report generation, data screening, data analysis and processing, and situation information generation.

[0004] The manual operation of STK software to generate satellite situation information has high learning costs and is prone to errors due to the complex functions, complicated interface and cumbersome operation of STK software. Especially when generating situation information of multiple satellites, the operation steps increase exponentially and the probability of error increases greatly. Non-professional operators use this method to generate situation information of multiple satellites with low efficiency and accuracy.

[0005] Writing third-party application software to automatically call STK software generation can achieve automated operation, but the third-party application software and STK software must be run simultaneously during the calculation process. In essence, it is still operating STK software. The calculation speed is limited by computer performance. When you need to view the simulation scene, you still have to operate STK software. The STK interface is complicated, the operation is cumbersome, the learning cost is high, and the operation is prone to errors. It is impossible to decouple the operator from the STK software;

[0006] The data generated by STK software is highly professional, and requires manual data screening, data analysis, and information aggregation for the reports generated by the software. It is difficult for non-professional users to filter out the desired data and convert it into concise and intuitive situation information, further reducing the efficiency of situation information generation. Summary of the invention

[0007] In order to solve the technical problem of how to improve the efficiency and accuracy of satellite situation information generation, the present invention provides a method for quickly generating satellite situation information, which solves the problems of cumbersome operation and easy errors in the process of operating STK software to calculate satellite situation information. The method uses STKX technology to complete the interconnection between QT and STK software, realizes the high integration of third-party application software and STK software, and solves the problem that it is difficult to decouple people and STK software. It enables users to achieve STK scene creation, multi-satellite addition, report generation, data screening and processing, data analysis and processing, and automation of situation information generation without learning STK software operation methods and steps, completes the rapid and accurate generation of multi-satellite situation information, and greatly improves the efficiency of situation information generation.

[0008] The purpose of the present invention is specifically achieved through the following technical solutions:

[0009] The present invention discloses a method for quickly generating satellite situation information, the method comprising:

[0010] Step 1: Embed the STKX component in STK into the graphical user interface of the QT third-party software in the form of an ActiveX control, thereby establishing an interconnection between QT and STK;

[0011] Step 2: Based on the task requirements, set the target parameters in the QT third-party software by modifying the configuration file;

[0012] Step 3: Based on the TCP (Transmission Control Protocol) protocol, the QT third-party software is used as the client to send a request to obtain target parameters to the server, and receive the target satellite orbit data corresponding to the target parameters in the satellite orbit database, thereby establishing a connection relationship between the QT third-party software and the satellite orbit database;

[0013] Step 4: The QT third-party software creates an STK scene through the ExecuteCommand() function provided by the STKX component, reads the configuration file, and adds the target satellite orbit data specified in the target parameters to the STK scene for display;

[0014] Step 5. The QT third-party software generates LLAPosition report, Classical Orbit Element report and AER report through the ExecuteCommand() function provided by the STKX component;

[0015] Through the LLA Position report, the orbital height at the specified time in the target satellite orbit data is automatically filtered out, and the drift rate and sub-satellite point longitude are obtained;

[0016] The Classical Orbit Element report can automatically filter out the orbital inclination of the target satellite at a specified time in the orbital data;

[0017] Through the AER report, the longitude of the sub-satellite point of the target rendezvous satellite at the closest distance in the target satellite orbit data is automatically screened out;

[0018] Step 6: Summarize the data in the LLA Position report, Classical Orbit Element report and AER report to obtain the situation information of a single satellite; determine whether the report data of all satellites in the mission requirements have been generated. If not, repeat step 5 to continue generating the report data of the next satellite. If it has been generated, proceed to step 7;

[0019] Step 7: Summarize the generated report data of all satellites, output and display the situation information of all satellites in the report data in the format of a text file, and realize the rapid generation of satellite situation information.

[0020] In step 1, the method to embed the STKX component in STK into the graphical user interface of the QT third-party software in the form of an ActiveX control is as follows:

[0021] Install the STK software, obtain the numbers of the 3D display control and the 2D display control of the STKX component in the system registry; embed the 3D display control and the 2D display control of the STKX component into the graphical user interface of the QT third-party software through the setControl() function of the QAxWidget class in QT; wherein the QT third-party software is a desktop application written using the QT platform.

[0022] In step 2, the target parameters include but are not limited to satellite name, satellite to be added, rendezvous satellite, satellite remaining fuel and / or custom text;

[0023] The configuration files include: a configuration file for satellites to be added, a configuration file for rendezvous satellites, a configuration file for remaining fuel and / or a custom text configuration file; wherein,

[0024] The satellite configuration file to be added is divided into two types: import in the form of six satellite numbers and import in the form of TLE files. It is used to set the target satellite to be added to the STK scene and match the satellite code or NORAD satellite number with the satellite name;

[0025] The rendezvous satellite configuration file is used to set the rendezvous information to be calculated for the target rendezvous satellite;

[0026] The remaining fuel configuration file is used to set the remaining fuel mass and remaining fuel information update time of the target satellite, and is matched and associated with the satellite name;

[0027] A custom text configuration file is used to set the text information to be added to the situation information file.

[0028] In step three, the connection relationship between the QT third-party software and the satellite orbit database is established through the TCP protocol socket programming interface provided by the QtcpSocket class in QT.

[0029] In step 4, the STK scene display forms include three-dimensional scene and two-dimensional scene. The three-dimensional scene is mainly used to display the satellite name and satellite orbit, and the two-dimensional scene is mainly used to display the satellite name and sub-satellite point trajectory. It is implemented through the display control controls in the STKX component, including three-dimensional scene display control controls and two-dimensional scene display control controls. Among them, the three-dimensional scene display control control is AGI Globe Control 11, and the two-dimensional scene display control control is AGI Map Control11.

[0030] In step five, the automatic screening method is: save the generated report locally in the form of a txt file, read the data at the specified location in the txt file through the open() function provided by the QFile class in QT, and realize automatic data screening.

[0031] In step 6, the method of summarizing the data in the LLA Position report, the Classical Orbit Element report and the AER report to obtain the situation information of a single satellite includes:

[0032] Determine whether the satellite orbit type is high orbit or low orbit. If it is a high orbit satellite, calculate the drift rate of the high orbit satellite, determine whether the high orbit satellite is in a fixed state or a drifting state based on the drift rate, and determine the drift direction of the high orbit satellite based on the height difference between the high orbit satellite and the geostationary orbit;

[0033] If it is a low-orbit satellite, the height difference between the perigee and apogee of the low-orbit satellite is calculated. If the height difference is less than the threshold, the low-orbit satellite is determined to be in a circular orbit, otherwise it is in an elliptical orbit.

[0034] In step 6, the drift rate is calculated as follows:

[0035] The high-orbit satellite orbits at an altitude of H kilometers from the geostationary orbit. Compared with the geostationary orbit satellite, the drift rate v p (degrees / day) is:

[0036]

[0037] Among them, a 0 is the semi-major axis of the geostationary orbit.

[0038] In step six, the method for judging whether the high-orbit satellite is in a fixed state or a drifting state according to the drift rate includes:

[0039] Affected by orbital perturbations, when |v p |When it is less than 0.1 degree / day, the high-orbit satellite is judged to be in a fixed state, otherwise it is judged to be in a drifting state; the high-orbit satellite fixed state means that at the same time every day, the longitude change of the high-orbit satellite sub-satellite point is stable within the threshold range; the high-orbit satellite drifting state means that at the same time every day, the longitude change of the high-orbit satellite sub-satellite point exceeds the threshold.

[0040] In step 6, the method for determining the drift direction of the high-orbit satellite includes:

[0041] When the orbital altitude of a high-orbit satellite is higher than that of the geostationary orbit, H is positive and v p When H is positive, it means that the high-orbit satellite is drifting westward relative to the geostationary orbit; when the orbital altitude of the high-orbit satellite is lower than the geostationary orbit altitude, H is negative, and v p A negative value indicates that the high-orbit satellite is drifting eastward relative to the geostationary orbit.

[0042] The beneficial effects of the present invention are:

[0043] 1. STKX components integrated with QT GUI

[0044] The STKX component is highly integrated into QT's GUI in the form of an ActiveX control, which realizes the organic combination of STK's powerful spatial task analysis and visualization capabilities with QT's GUI development capabilities. Through QT, secondary development and functional expansion of the STKX component functions are realized, solving the problem of the difficulty in decoupling users and STK software.

[0045] 2.Multi-type and highly flexible configuration interface

[0046] Various types of configuration files are designed, and the formats of each type of configuration files are defined. Through a highly flexible configuration interface, the matching association between satellite codes or NORAD satellite numbers and satellite names, and the matching association between satellite names and remaining fuel information are completed. It is also possible to configure on demand which satellites are added to the scene and which satellites’ rendezvous information is generated.

[0047] 3. Orbital data automatic acquisition interface

[0048] An efficient data interface based on C / S architecture and TCP protocol was designed and implemented. This interface can connect QT with the orbit database. By sending orbit data acquisition requests by the client, the server reading database data and returning orbit data, and the client receiving orbit data, the required data can be obtained from the database in real time and accurately, providing a basis for subsequent situation data generation.

[0049] 4. Rapid generation of multi-satellite situation information

[0050] The present invention uses a program to automatically call STKX components to replace manual operation of STK software generation. The designed multi-satellite situation data rapid generation process and report data classification processing process are based on the configuration file setting parameters and orbit data as input. After the "one-key start" calculation, the whole process does not require human intervention and there is no need to open the STK software. The software automatically calls the STKX components to complete a series of operations such as scene creation, satellite addition, and report calculation, thereby realizing the full process automation from orbit data to situation information generation and saving the time of operating the software.

[0051] 5. Classification and processing of report data

[0052] Distinguish between the two different orbit types of high orbit and low orbit, classify and process the report data, and perform secondary processing based on the report data to determine the fixed or drifting status of the high-orbit satellite and the orbit type of the low-orbit satellite to obtain more intuitive situation information.

[0053] 6. Comprehensive display and interaction of situation information

[0054] By utilizing QT's powerful interface design capabilities and STKX's 2D and 3D visualization capabilities, a visualization of multi-satellite situation information is realized. While providing "one-click start" generation, it also provides interactive interfaces such as scene control, simulation control, and manual data import, making it easy for users to adjust satellite parameters and understand the situation of multiple satellites.

[0055] 7. High accuracy

[0056] Compared with the manual operation of STK software generation, the use of the present invention can avoid the problems of misoperation and missed operation caused by manual operation of STK software, manual screening of data, and manual analysis and processing of data. It has high accuracy. Taking 400 sets of orbital data as input, 400 sets of situation information are generated using the present invention, and the calculation accuracy is 100%.

[0057] 8. Good human-machine applicability

[0058] Through the high integration of STKX components and QT GUI, the complex STK software operation logic is transformed into easy-to-understand and easy-to-operate custom GUI operation logic, so that users do not need to face the complicated STK software interface, and the decoupling of users and STK software is achieved, so that non-professional users can also quickly get started.

[0059] 9. Strong scalability

[0060] The multi-type and highly flexible configuration file interface designed by the present invention supports on-demand configuration of satellites to be added, rendezvous satellites, remaining fuel, and custom text. By modifying the configuration file, the changes in the number of satellites, rendezvous satellites, remaining fuel, custom text, etc. can be adapted without changing the program or process. BRIEF DESCRIPTION OF THE DRAWINGS

[0061] The present invention is further described in detail below based on the accompanying drawings and embodiments.

[0062] Figure 1 The present invention provides a schematic flow chart of a method for rapidly generating satellite situation information.

[0063] Figure 2 The figure is a schematic diagram of the information interface when the present invention is used to calculate multi-satellite situation information.

[0064] Figure 3 Schematic diagram of the graphical user interface of the QT third-party software designed for the present invention. DETAILED DESCRIPTION

[0065] like Figure 1-3 As shown, an embodiment of the present invention provides a method for quickly generating satellite situation information, which is suitable for automatically generating common situation information of multiple satellites. The method includes:

[0066] Step 1: Embed the STKX component in the Satellite Tool Kit (STK) into the Graphical User Interface (GUI) of the QT third-party software in the form of an ActiveX control, thereby establishing the interconnection between QT and STK, such as Figure 3 As shown, the 3D earth display and 2D map ActiveX controls are embedded in the graphical user interface;

[0067] Step 2: Based on the task requirements, set the target parameters in the QT third-party software by modifying the configuration file;

[0068] Step 3: Based on the Transmission Control Protocol (TCP), the QT third-party software is used as the client to send a request to obtain target parameters to the server, and the target satellite orbit data corresponding to the target parameters in the satellite orbit database is received, thereby establishing a connection relationship between the QT third-party software and the satellite orbit database;

[0069] Step 4. The QT third-party software creates an STK scene through the ExecuteCommand() function provided by the STKX component, reads the configuration file, and adds the target satellite orbit data specified in the target parameters to the STK scene for display, such as Figure 3 As shown, all satellite orbits added to the STK scene are displayed, and the remaining fuel and orbital epoch time of all satellites are displayed in a table format;

[0070] Step 5. The QT third-party software generates the Latitude Longitude Altitude Position (LLAPosition) report, the Classical Orbit Element (COE) report and the Azimuth Elevation Range (AER) report through the ExecuteCommand() function provided by the STKX component;

[0071] Through the LLA Position report, the orbital height at the specified time in the target satellite orbit data is automatically filtered out, and the drift rate and sub-satellite point longitude are obtained;

[0072] The Classical Orbit Element report can automatically filter out the orbital inclination of the target satellite at a specified time in the orbital data;

[0073] Through the AER report, the longitude of the sub-satellite point of the target rendezvous satellite at the closest distance in the target satellite orbit data is automatically screened out;

[0074] Step 6: Summarize the data in the LLA Position report, Classical Orbit Element report and AER report to obtain the situation information of a single satellite; determine whether the report data of all satellites in the mission requirements have been generated. If not, repeat step 5 to continue generating the report data of the next satellite. If it has been generated, proceed to step 7;

[0075] Step 7: Summarize the generated report data of all satellites, output and display the situation information of all satellites in the report data in the format of a text file, and realize the rapid generation of satellite situation information.

[0076] In step 1, the method to embed the STKX component in STK into the graphical user interface of the QT third-party software in the form of an ActiveX control is as follows:

[0077] Install the STK software, obtain the numbers of the 3D display control and the 2D display control of the STKX component in the system registry; embed the 3D display control and the 2D display control of the STKX component into the graphical user interface of the QT third-party software through the setControl() function of the QAxWidget class in QT; wherein the QT third-party software is a desktop application written using the QT platform.

[0078] In step 2, the target parameters include but are not limited to satellite name, satellite to be added, rendezvous satellite, satellite remaining fuel and / or custom text;

[0079] The configuration files include: a configuration file for satellites to be added, a configuration file for rendezvous satellites, a configuration file for remaining fuel and / or a custom text configuration file; wherein,

[0080] The satellite configuration file to be added is divided into two types: import in the form of six satellite numbers and import in the form of TLE files. It is used to set the target satellite to be added to the STK scene and match the satellite code or NORAD satellite number with the satellite name;

[0081] The rendezvous satellite configuration file is used to set the rendezvous information to be calculated for the target rendezvous satellite;

[0082] The remaining fuel configuration file is used to set the remaining fuel mass and remaining fuel information update time of the target satellite, and is matched and associated with the satellite name;

[0083] A custom text configuration file is used to set the text information to be added to the situation information file.

[0084] The content format of each configuration file is shown in Table 1:

[0085] Table 1

[0086]

[0087]

[0088] In step 3, the connection between the QT third-party software and the satellite orbit database is established through the TCP protocol socket programming interface provided by the QtcpSocket class in QT. The codes related to data request and data content reading during sending are shown in Table 2:

[0089] Table 2

[0090]

[0091] In step 4, the STK scene display forms include 3D and 2D, which are realized through the display control controls in the STKX component, including 3D scene display control controls and 2D scene display control controls. Among them, the 3D scene display control control is AGI Globe Control 11, and the 2D scene display control control is AGI Map Control 11.

[0092] The three-dimensional scene focuses on displaying the satellite name and satellite orbit, while the two-dimensional scene focuses on displaying the satellite name and sub-satellite point trajectory.

[0093] In step five, the automatic screening method is: save the generated report locally in the form of a txt file, read the data at the specified location in the txt file through the open() function provided by the QFile class in QT, and realize automatic data screening.

[0094] In steps 4 and 5, the third-party software issues commands through the ExecuteCommand() function provided by STKX. The command contents and formats for scene creation, satellite addition, and report generation are shown in Table 3:

[0095] Table 3

[0096]

[0097]

[0098] In step 6, the method of summarizing the data in the LLA Position report, the Classical Orbit Element report and the AER report to obtain the situation information of a single satellite includes:

[0099] Determine whether the satellite orbit type is high orbit or low orbit. If it is a high orbit satellite, calculate the drift rate of the high orbit satellite, determine whether the high orbit satellite is in a fixed state or a drifting state based on the drift rate, and determine the drift direction of the high orbit satellite based on the height difference between the high orbit satellite and the geostationary orbit;

[0100] If it is a low-orbit satellite, the height difference between the perigee and apogee of the low-orbit satellite is calculated. If the height difference is less than the threshold, the low-orbit satellite is determined to be in a circular orbit, otherwise it is in an elliptical orbit.

[0101] In step 6, the drift rate is calculated as follows:

[0102] The high-orbit satellite orbits at an altitude of H kilometers from the geostationary orbit. Compared with the geostationary orbit satellite, the drift rate v p (degrees / day) is:

[0103]

[0104] Among them, a 0 is the semi-major axis of the geostationary orbit.

[0105] In step six, the method for judging whether the high-orbit satellite is in a fixed state or a drifting state according to the drift rate includes:

[0106] Affected by orbital perturbations, when |v p|When it is less than 0.1 degree / day, the high-orbit satellite is judged to be in a fixed state, otherwise it is judged to be in a drifting state; the high-orbit satellite fixed state means that at the same time every day, the longitude change of the high-orbit satellite sub-satellite point is stable within the threshold range; the high-orbit satellite drifting state means that at the same time every day, the longitude change of the high-orbit satellite sub-satellite point exceeds the threshold.

[0107] In step 6, the method for determining the drift direction of the high-orbit satellite includes:

[0108] When the orbital altitude of a high-orbit satellite is higher than that of the geostationary orbit, H is positive and v p When H is positive, it means that the high-orbit satellite is drifting westward relative to the geostationary orbit; when the orbital altitude of the high-orbit satellite is lower than the geostationary orbit altitude, H is negative, and v p A negative value indicates that the high-orbit satellite is drifting eastward relative to the geostationary orbit.

[0109] The present invention uses a program to automatically call the STKX component to generate instead of manually operating the STK software to generate, and designs a multi-satellite situation data rapid generation process and a report data classification processing process, which saves the time of operating the software. It takes about 145 seconds to manually operate the STK software to generate the situation information of two satellites. The time consumption of the main steps of manually operating the STK software to generate the situation information of two satellites is shown in Table 4.

[0110] Table 4

[0111]

[0112]

[0113] Therefore, it takes about 36 minutes to manually operate the STK software to generate the situation information of 30 satellites. It is measured that it only takes about 10 seconds to use the present invention to generate the situation information of 30 satellites, which is only 0.46% of the time taken by manually operating the STK software to generate the situation information, and the generation speed is significantly improved.

[0114] In order to illustrate the technical solution of the present invention, specific application examples are provided as follows:

[0115] Using the third-party application software designed by the present invention, the calculation of 15 high-orbit satellites, 15 low-orbit satellites, and 3 groups of intersection relationships is used as an example to illustrate:

[0116] 1. Verify scene settings

[0117] (1) Number of orbital elements

[0118] The six orbit numbers of 10 high-orbit satellites and 10 low-orbit satellites are shown in Table 5:

[0119] Table 5

[0120]

[0121]

[0122] The number of TLE elements of 5 high-orbit satellites and 5 low-orbit satellites is shown in Table 6:

[0123] Table 6

[0124]

[0125]

[0126]

[0127] (2) Simulation time

[0128] Beijing time: 12:00:00, August 11, 2024 - 12:00:00, August 14, 2024.

[0129] (3) Configuration file settings

[0130] Modify the configuration files of the satellites to be added (six satellites), the configuration files of the rendezvous satellites, the configuration files of the remaining fuel, and the configuration files of the custom texts as shown in Table 7:

[0131] Table 7

[0132]

[0133]

[0134]

[0135]

[0136] 2. Calculation results

[0137] After starting the "one-key calculation", the calculation time is about 8 seconds, and the situation information is as follows:

[0138] The A01 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in geosynchronous orbit, with an orbit altitude of about 35829.99 kilometers and an orbit inclination of about 0.14 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 89.83 degrees west longitude, and the remaining fuel is 450.60 kg (the remaining fuel update time is 2024-08-10 10:30:00);

[0139] The A02 satellite (epoch time 2024-08-10 12:00:00.000) is currently about 100.12 kilometers below the geosynchronous orbit, with an orbital altitude of about 35730.04 kilometers, drifting eastward at a rate of about 1.28 degrees / day, with an orbital inclination of about 0.14 degrees. At 12:00 on August 11, the subsatellite point longitude was about 59.45 degrees west longitude, and the remaining fuel was 458.02 kg (the remaining fuel was updated at 2023-08-09 12:00:00);

[0140] The A03 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in geosynchronous orbit, with an orbital altitude of about 35830.16 kilometers and an orbital inclination of about 15.00 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 34.90 degrees west longitude, and the remaining fuel is 123.56 kg (the remaining fuel update time is 2023-08-05 20:00:00);

[0141] The A04 satellite (epoch time 2024-08-10 12:00:00.000) is currently about 99.76 kilometers above the geosynchronous orbit, with an orbit altitude of about 35888.67 kilometers, drifting westward at a rate of about 1.28 degrees / day, with an orbit inclination of about 0.14 degrees. At 12:00 on August 11, the subsatellite point longitude was about 39.39 degrees west longitude, and the remaining fuel was 203.65 kg (the remaining fuel was updated at 2023-08-08 08:00:00);

[0142] The A05 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in geosynchronous orbit, with an orbit altitude of about 35781.92 kilometers and an orbit inclination of about 3.00 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 7.50 degrees west longitude, and the remaining fuel is 50.42 kg (the remaining fuel update time is 2023-08-08 08:00:00);

[0143] The A06 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in geosynchronous orbit, with an orbit altitude of about 35788.39 kilometers and an orbit inclination of about 3.00 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 6.68 degrees west longitude, and the remaining fuel is 30.69 kg (the remaining fuel update time is 2024-08-09 08:00:00);

[0144] The A07 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in the geosynchronous orbit, with an orbit altitude of about 35787.89 kilometers and an orbit inclination of about 0.14 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 23.98 degrees east longitude, and the remaining fuel is 45.68 kg (the remaining fuel update time is 2024-08-09 08:00:00);

[0145] The A08 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in geosynchronous orbit, with an orbit altitude of about 35829.50 kilometers and an orbit inclination of about 5.00 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 84.60 degrees east longitude, and the remaining fuel is 410.25 kg (the remaining fuel update time is 2024-08-09 08:00:00);

[0146] The A09 satellite (epoch time 2024-08-10 12:00:00.000) is fixed in geosynchronous orbit, with an orbit altitude of about 35788.13 kilometers and an orbit inclination of about 0.14 degrees. The longitude of the subsatellite point at 12:00 on August 11 is about 115.58 degrees east longitude, and the remaining fuel is 326.05 kg (the remaining fuel update time is 2024-08-09 08:00:00);

[0147] The A10 satellite (epoch time 2024-08-10 12:00:00.000) is currently about 60.30 kilometers below the geosynchronous orbit, with an orbit altitude of about 35728.14 kilometers, drifting eastward at a rate of about 0.77 degrees / day, with an orbit inclination of about 0.14 degrees. At 12:00 on August 11, the subsatellite point longitude was about 149.66 degrees east longitude, and the remaining fuel was 453.01 kg (the remaining fuel was updated at 2024-08-09 08:00:00);

[0148] The B01 satellite (epoch time 1967-10-29 08:00:00.000) was fixed in geosynchronous orbit with an orbital inclination of about 38.95 degrees. The subsatellite longitude at 12:00 on August 11 was about 169.63 degrees west longitude, with 128.09 kg of remaining fuel;

[0149] The B02 satellite (epoch time 1967-10-29 08:00:00.000) is currently about 13.89 kilometers above the geosynchronous orbit, with an orbit altitude of about 35812.18 kilometers, drifting westward at a rate of about 0.18 degrees / day, with an orbit inclination of about 34.80 degrees. At 12:00 on August 11, the subsatellite point longitude was about 161.10 degrees west longitude, and the remaining fuel was 136.85 kg;

[0150] The B03 satellite (epoch time 1967-10-29 08:00:00.000) is fixed in geosynchronous orbit with an orbital inclination of about 23.17 degrees. The subsatellite longitude at 12:00 on August 11 was about 134.31 degrees west longitude, with 203.47 kg of remaining fuel;

[0151] The B04 satellite (epoch time 1967-10-29 08:00:00.000) is fixed in geosynchronous orbit with an orbital inclination of about 58.99 degrees. The subsatellite longitude at 12:00 on August 11 was about 149.28 degrees west longitude, with 845.02 kg of remaining fuel;

[0152] The B05 satellite (epoch time 1967-10-29 08:00:00.000) is currently about 10.43 kilometers above the geosynchronous orbit, with an orbit altitude of about 35805.77 kilometers, drifting westward at a rate of about 0.13 degrees / day, with an orbit inclination of about 31.06 degrees. At 12:00 on August 11, the subsatellite point longitude was about 91.86 degrees west longitude, and the remaining fuel was 52.36 kg;

[0153] The C01 satellite is in a circular orbit at an altitude of about 300 kilometers, with 78.65 kg of remaining fuel (remaining fuel update time 2024-08-10 10:30:00);

[0154] The C02 satellite is in a circular orbit at an altitude of about 300 kilometers, with 45.63 kg of remaining fuel (remaining fuel update time 2023-08-09 12:00:00);

[0155] The C03 satellite is in a circular orbit at an altitude of about 300 kilometers, with 48.06 kg of remaining fuel (remaining fuel update time 2023-08-05 20:00:00);

[0156] The C04 satellite is in a circular orbit at an altitude of about 300 kilometers, with 89.56 kg of remaining fuel (remaining fuel update time 2023-08-08 08:00:00);

[0157] The C05 satellite is in a circular orbit at an altitude of about 300 kilometers, with 114.56 kg of remaining fuel (remaining fuel update time 2023-08-08 08:00:00);

[0158] The C06 satellite is in a circular orbit at an altitude of about 400 kilometers, with 111.87 kg of remaining fuel (remaining fuel update time 2024-08-09 08:00:00);

[0159] The C07 satellite is in a circular orbit at an altitude of about 400 kilometers, with 52.06 kg of remaining fuel (remaining fuel update time 2024-08-09 08:00:00);

[0160] The C08 satellite is in a circular orbit at an altitude of about 400 kilometers, with 41.75 kg of remaining fuel (remaining fuel update time 2024-08-09 08:00:00);

[0161] The C09 satellite is in a circular orbit at an altitude of about 400 kilometers, with 136.52 kg of remaining fuel (remaining fuel update time 2024-08-09 08:00:00);

[0162] The C10 satellite is in a circular orbit at an altitude of about 400 km, with 135.23 kg of fuel remaining (remaining fuel update time 2024-08-09 08:00:00);

[0163] The D01 satellite is in a circular orbit at an altitude of about 602 kilometers, with 85.02 kg of remaining fuel (remaining fuel update time 2024-08-09 08:00:00);

[0164] The D02 satellite is operating in an elliptical orbit with a perigee of about 415 kilometers and an apogee of about 749 kilometers, with 74.03 kg of remaining fuel (the remaining fuel will be updated on 2024-08-09 08:00:00);

[0165] The D03 satellite is operating in an elliptical orbit with a perigee of about 606 kilometers and an apogee of about 613 kilometers, with 41.63 kg of remaining fuel (the remaining fuel will be updated on 2024-08-09 08:00:00);

[0166] The D04 satellite is operating in an elliptical orbit with a perigee of about 436 kilometers and an apogee of about 771 kilometers, with 45.85 kg of remaining fuel (the remaining fuel will be updated on 2024-08-09 08:00:00);

[0167] The D05 satellite is operating in an elliptical orbit with a perigee of about 606 kilometers and an apogee of about 612 kilometers, with 50.86 kg of remaining fuel (the remaining fuel will be updated on 2024-08-09 08:00:00);

[0168] At 12:00 on August 11, the distance between A01 and A03 satellites was about 38985.60 kilometers. From 12:00 on August 11 to 12:00 on August 14, the closest distance between the two satellites was 2024-08-12 00:50:42.428, with a minimum distance of about 38829.73 kilometers. At the time of the minimum distance, the longitude of the subsatellite point of A01 satellite was about 89.78 degrees west longitude, and the longitude of the subsatellite point of A03 satellite was about 35.18 degrees west longitude.

[0169] At 12:00 on August 11, the distance between A06 and B05 was about 56674.70 km. From 12:00 on August 11 to 12:00 on August 14, the closest distance between the two satellites was 2024-08-11 16:49:08.602, with a minimum distance of about 53019.39 km. At the time of the minimum distance, the longitude of the subsatellite point of A06 satellite was about 6.70 degrees west longitude, and the longitude of the subsatellite point of B05 satellite was about 83.81 degrees west longitude.

[0170] At 12:00 on August 11, the distance between B01 and B02 was about 28,376.81 kilometers. From 12:00 on August 11 to 12:00 on August 14, the closest distance between the two satellites was 2024-08-14 02:24:07.933, with a minimum distance of about 12,038.15 kilometers. At the time of the minimum distance, the longitude of the subsatellite point of B01 was about 177.15 degrees west longitude, and the longitude of the subsatellite point of B02 was about 159.81 degrees west longitude.

[0171] Note: This file is automatically generated using the technical solution disclosed in this invention.

[0172] 3. Time consumption statistics

[0173] It takes about 10 seconds to generate the situation information of the above 30 satellites, which is only 0.46% of the time (about 36 minutes) taken by manually operating the STK software to generate the situation information of 30 satellites, thus achieving the effect of rapid generation of situation information.

[0174] The beneficial effects of the embodiments of the present invention are:

[0175] 1. STKX components integrated with QT GUI

[0176] The STKX component is highly integrated into QT's GUI in the form of an ActiveX control, which realizes the organic combination of STK's powerful spatial task analysis and visualization capabilities with QT's GUI development capabilities. Through QT, secondary development and functional expansion of the STKX component functions are realized, solving the problem of the difficulty in decoupling users and STK software.

[0177] 2.Multi-type and highly flexible configuration interface

[0178] Various types of configuration files are designed, and the formats of each type of configuration files are defined. Through a highly flexible configuration interface, the matching association between satellite codes or NORAD satellite numbers and satellite names, and the matching association between satellite names and remaining fuel information are completed. It is also possible to configure on demand which satellites are added to the scene and which satellites’ rendezvous information is generated.

[0179] 3. Orbital data automatic acquisition interface

[0180] An efficient data interface based on C / S architecture and TCP protocol was designed and implemented. This interface can connect QT with the orbit database. By sending orbit data acquisition requests by the client, the server reading database data and returning orbit data, and the client receiving orbit data, the required data can be obtained from the database in real time and accurately, providing a basis for subsequent situation data generation.

[0181] 4. Rapid generation of multi-satellite situation information

[0182] The present invention uses a program to automatically call STKX components to replace manual operation of STK software generation. The designed multi-satellite situation data rapid generation process and report data classification processing process are based on the configuration file setting parameters and orbit data as input. After the "one-key start" calculation, the whole process does not require human intervention and there is no need to open the STK software. The software automatically calls the STKX components to complete a series of operations such as scene creation, satellite addition, and report calculation, thereby realizing the full process automation from orbit data to situation information generation and saving the time of operating the software.

[0183] 5. Classification and processing of report data

[0184] Distinguish between the two different orbit types of high orbit and low orbit, classify and process the report data, and perform secondary processing based on the report data to determine the fixed or drifting status of the high-orbit satellite and the orbit type of the low-orbit satellite to obtain more intuitive situation information.

[0185] 6. Comprehensive display and interaction of situation information

[0186] By utilizing QT's powerful interface design capabilities and STKX's 2D and 3D visualization capabilities, a visualization of multi-satellite situation information is realized. While providing "one-click start" generation, it also provides interactive interfaces such as scene control, simulation control, and manual data import, making it easy for users to adjust satellite parameters and understand the situation of multiple satellites.

[0187] 7. High accuracy

[0188] Compared with the manual operation of STK software generation, the use of the present invention can avoid the problems of misoperation and missed operation caused by manual operation of STK software, manual screening of data, and manual analysis and processing of data. It has high accuracy. Taking 400 sets of orbital data as input, 400 sets of situation information are generated using the present invention, and the calculation accuracy is 100%.

[0189] 8. Good human-machine applicability

[0190] Through the high integration of STKX components and QT GUI, the complex STK software operation logic is transformed into easy-to-understand and easy-to-operate custom GUI operation logic, so that users do not need to face the complicated STK software interface, and the decoupling of users and STK software is achieved, so that non-professional users can also quickly get started.

[0191] 9. Strong scalability

[0192] The multi-type and highly flexible configuration file interface designed by the present invention supports on-demand configuration of satellites to be added, rendezvous satellites, remaining fuel, and custom text. By modifying the configuration file, the changes in the number of satellites, rendezvous satellites, remaining fuel, custom text, etc. can be adapted without changing the program or process.

[0193] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A method for quickly generating satellite situation information, characterized in that: The method includes: Step 1: Embed the STKX component in STK into the graphical user interface of the QT third-party software in the form of an ActiveX control, thereby establishing an interconnection between QT and STK; Step 2: Based on the task requirements, set the target parameters in the QT third-party software by modifying the configuration file; Step 3: Based on the TCP protocol, the QT third-party software is used as the client to send a request to obtain target parameters to the server, and the target satellite orbit data corresponding to the target parameters in the satellite orbit database is received, thereby establishing a connection relationship between the QT third-party software and the satellite orbit database; Step 4: The QT third-party software creates an STK scene through the ExecuteCommand() function provided by the STKX component, reads the configuration file, and adds the target satellite orbit data specified in the target parameters to the STK scene for display; Step 5. The QT third-party software generates LLA Position report, Classical Orbit Element report and AER report through the ExecuteCommand() function provided by the STKX component; Through the LLA Position report, the orbital height at the specified time in the target satellite orbit data is automatically filtered out, and the drift rate and sub-satellite point longitude are obtained; The Classical Orbit Element report can automatically filter out the orbital inclination of the target satellite at a specified time in the orbital data; Through the AER report, the longitude of the sub-satellite point of the target rendezvous satellite at the closest distance in the target satellite orbit data is automatically screened out; Step 6: Summarize the data in the LLA Position report, Classical Orbit Element report and AER report to obtain the situation information of a single satellite; determine whether the report data of all satellites in the mission requirements have been generated. If not, repeat step 5 to continue generating the report data of the next satellite. If it has been generated, proceed to step 7; Step 7: Summarize the generated report data of all satellites, output and display the situation information of all satellites in the report data in the format of a text file, and realize the rapid generation of satellite situation information.

2. The method according to claim 1, characterized in that In step 1, the method to embed the STKX component in STK into the graphical user interface of the QT third-party software in the form of an ActiveX control is as follows: Install the STK software, obtain the numbers of the 3D display control and the 2D display control of the STKX component in the system registry; embed the 3D display control and the 2D display control of the STKX component into the graphical user interface of the QT third-party software through the setControl() function of the QAxWidget class in QT; wherein the QT third-party software is a desktop application written using the QT platform.

3. The method according to claim 1, characterized in that In step 2, the target parameters include but are not limited to satellite name, satellite to be added, rendezvous satellite, satellite remaining fuel and / or custom text; The configuration files include: a configuration file for satellites to be added, a configuration file for rendezvous satellites, a configuration file for remaining fuel and / or a custom text configuration file; wherein, The satellite configuration file to be added is divided into two types: import in the form of six satellite numbers and import in the form of TLE files. It is used to set the target satellite to be added to the STK scene and match the satellite code or NORAD satellite number with the satellite name; The rendezvous satellite configuration file is used to set the rendezvous information to be calculated for the target rendezvous satellite; The remaining fuel configuration file is used to set the remaining fuel mass and remaining fuel information update time of the target satellite, and is matched and associated with the satellite name; A custom text configuration file is used to set the text information to be added to the situation information file.

4. The method according to claim 1, characterized in that In step three, the connection relationship between the QT third-party software and the satellite orbit database is established through the TCP protocol socket programming interface provided by the QtcpSocket class in QT.

5. The method according to claim 1, characterized in that In step 4, the STK scene display forms include three-dimensional scene and two-dimensional scene. The three-dimensional scene is mainly used to display the satellite name and satellite orbit, and the two-dimensional scene is mainly used to display the satellite name and sub-satellite point trajectory. It is implemented through the display control controls in the STKX component, including three-dimensional scene display control controls and two-dimensional scene display control controls. Among them, the three-dimensional scene display control control is AGI Globe Control 11, and the two-dimensional scene display control control is AGI Map Control 11.

6. The method according to claim 1, characterized in that In step five, the automatic screening method is: save the generated report locally in the form of a txt file, read the data at the specified location in the txt file through the open() function provided by the QFile class in QT, and realize automatic data screening.

7. The method according to claim 1, characterized in that In step 6, the method of summarizing the data in the LLA Position report, the Classical Orbit Element report and the AER report to obtain the situation information of a single satellite includes: Determine whether the satellite orbit type is high orbit or low orbit. If it is a high orbit satellite, calculate the drift rate of the high orbit satellite, determine whether the high orbit satellite is in a fixed state or a drifting state based on the drift rate, and determine the drift direction of the high orbit satellite based on the height difference between the high orbit satellite and the geostationary orbit; If it is a low-orbit satellite, the height difference between the perigee and apogee of the low-orbit satellite is calculated. If the height difference is less than the threshold, the low-orbit satellite is determined to be in a circular orbit, otherwise it is in an elliptical orbit.

8. The method according to claim 7, characterized in that In step 6, the drift rate is calculated as follows: The high-orbit satellite orbits at an altitude of H kilometers from the geostationary orbit. Compared with the geostationary orbit satellite, the drift rate v p (degrees / day) is: Where a0 is the semi-major axis of the geostationary orbit.

9. The method according to claim 8, characterized in that In step six, the method for judging whether the high-orbit satellite is in a fixed state or a drifting state according to the drift rate includes: Affected by orbital perturbations, when |v p |When it is less than 0.1 degree / day, the high-orbit satellite is judged to be in a fixed state, otherwise it is judged to be in a drifting state; the high-orbit satellite fixed state means that at the same time every day, the longitude change of the high-orbit satellite sub-satellite point is stable within the threshold range; the high-orbit satellite drifting state means that at the same time every day, the longitude change of the high-orbit satellite sub-satellite point exceeds the threshold.

10. The method according to claim 8, characterized in that In step 6, the method for determining the drift direction of the high-orbit satellite includes: When the orbital altitude of a high-orbit satellite is higher than that of the geostationary orbit, H is positive and v p When H is positive, it means that the high-orbit satellite is drifting westward relative to the geostationary orbit; when the orbital altitude of the high-orbit satellite is lower than the geostationary orbit altitude, H is negative, and v p A negative value indicates that the high-orbit satellite is drifting eastward relative to the geostationary orbit.

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