A method for quickly generating satellite situation information

Abstract

The present invention discloses a method for quickly generating satellite situation information, which solves the problem of how to improve the generation efficiency and accuracy of satellite situation information; it belongs to the field of satellite situation information generation; it includes: embedding the STKX component in STK into the GUI of the QT third-party software interface in the form of an ActiveX control; setting the target parameters in the QT third-party software interface by modifying the configuration file; based on the TCP protocol, using the QT third-party software as the client, sending a request to obtain target parameters to the server, and receiving the target satellite orbit data corresponding to the target parameters in the satellite orbit database; the QT third-party software creates an STK scene through the ExecuteCommand() function provided by the STKX component, adds the target satellite orbit data specified in the target parameters to the STK scene for display, generates and summarizes the data in the report to obtain the situation information of all satellites, and realizes the quick generation of satellite situation information; the present invention completes the quick and accurate generation of multi-satellite situation information, and greatly improves the generation efficiency of situation information.

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] 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 error in the process of calculating satellite situation information by operating STK software. This 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, breaks the difficult problem of decoupling between humans and STK software, enables users to automate STK scenario creation, multi-satellite addition, report generation, data screening and processing, data analysis and processing, and situation information generation without learning the operation methods and steps of STK software, and completes the rapid and accurate generation of multi-satellite situation information, greatly improving the efficiency of situation information generation.

[0008] The object of the present invention is specifically realized through the following technical solutions:

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

[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 relationship 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, use the QT third-party software as the client to send a request for obtaining 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 scenario 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 scenario for display;

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

[0015] Through the LLA Position report, automatically screen out the orbital altitude at the specified moment in the target satellite orbit data, and obtain the drift rate and sub-satellite point longitude;

[0016] Automatically screen out the orbital inclination at a specified moment in the target satellite orbit data through the Classical Orbit Element report;

[0017] Automatically screen out the sub-satellite point longitude of the target rendezvous satellite at the moment of the closest distance in the target satellite orbit data through the AER report;

[0018] Step 6: Aggregate 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: Aggregate the report data of all generated satellites, output and display the situation information of all satellites in the report data in the format of a text file, and achieve the rapid generation of satellite situation information.

[0020] In Step 1, the method of embedding 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, and obtain the numbers of the 3D display control and 2D display control of the STKX component in the system registry; Through the setControl() function of the QAxWidget class in QT, embed the 3D display control and 2D display control of the STKX component into the graphical user interface of the QT third-party software; Among them, 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, remaining fuel of the satellite, and / or custom text;

[0023] The configuration files include: configuration file for satellite to be added, configuration file for rendezvous satellite, configuration file for remaining fuel, and / or configuration file for custom text; Among them,

[0024] The configuration file for the satellite to be added is divided into two types: imported in the form of six orbital elements and imported in the form of a TLE file, which is used to set the target satellite to be added to the STK scenario, and match and associate the satellite code or NORAD satellite number with the satellite name;

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

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

[0027] A custom text configuration file for setting the text information to be added to the situation information file.

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

[0029] In step four, the STK scene display forms include two types: 3D scene and 2D scene. The 3D scene is mainly used to display the satellite name and satellite orbit, and the 2D scene is mainly used to display the satellite name and sub-satellite point track; it is implemented through the display control controls in the STKX component, including the 3D scene display control control and the 2D scene display control control. Among them, the 3D scene display control control is AGI Globe Control 11, and the 2D scene display control control is AGI Map Control11.

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

[0031] In step six, the methods for summarizing the data in the LLA Position report, Classical Orbit Element report, and AER report to obtain the situation information of a single satellite include:

[0032] Judge 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, judge whether the high-orbit satellite is in a fixed state or a drifting state based on the drift rate, and judge the drifting 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, calculate the height difference between the perigee and apogee of the low-orbit satellite. If the height difference is less than the threshold, it is determined that the low-orbit satellite is in a circular orbit, otherwise it is in an elliptical orbit.

[0034] In step six, the calculation method of the drift rate is as follows:

[0035] The high-orbit satellite operates on an orbit at a height 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, a0 is the semi-major axis of the geostationary orbit.

[0038] In step six, the method for determining whether the geosynchronous satellite is in a fixed-point state or a drifting state based on the drift rate includes:

[0039] Affected by orbital perturbation, when |v p | is less than 0.1 degree per day, it is determined that the geosynchronous satellite is in a fixed-point state; otherwise, it is determined that the geosynchronous satellite is in a drifting state. Among them, the fixed-point state of the geosynchronous satellite means that at the same moment every day, the longitude change of the sub-satellite point of the geosynchronous satellite is stable within the threshold range; the drifting state of the geosynchronous satellite means that at the same moment every day, the longitude change of the sub-satellite point of the geosynchronous satellite exceeds the threshold.

[0040] In step six, the method for determining the drifting direction of the geosynchronous satellite includes:

[0041] When the orbital altitude of the geosynchronous satellite is higher than the altitude of the geostationary orbit, H is positive, and v p is positive, indicating that the geosynchronous satellite drifts westward relative to the geostationary orbit; when the orbital altitude of the geosynchronous satellite is lower than the altitude of the geostationary orbit, H is negative, and v p is negative, indicating that the geosynchronous satellite drifts eastward relative to the geostationary orbit.

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

[0043] 1. Integration of STKX component and QT GUI

[0044] The STKX component is highly integrated into the GUI of QT in the form of an ActiveX control, realizing the organic combination of the powerful space mission analysis and visualization capabilities of STK and the GUI development capabilities of QT. Through QT, secondary development and function expansion of the functions of the STKX component are achieved, and the problem that it is difficult for users to decouple from the STK software is solved.

[0045] 2. Multi-type highly flexible configuration interfaces

[0046] A variety of types of configuration files are designed, and the format of each type of configuration file is defined. Through the highly flexible configuration interface, the matching association between the satellite code or NORAD satellite number and the satellite name, and the matching association between the satellite name and the remaining fuel information are completed. It is configured as needed which satellites are added to the scenario and which rendezvous information between satellites is generated.

[0047] 3. Automatic acquisition interface for orbital data

[0048] An efficient data interface based on the C / S architecture and TCP protocol is designed and implemented. This interface can connect QT to the orbital database. By means of the client sending a request for obtaining orbital data, the server reading the database data and returning the orbital data, and the client receiving the orbital data, the required data can be obtained from the database in real time and accurately, providing a basis for the subsequent generation of situational data.

[0049] 4. Rapid Generation of Multi-Satellite Situation Information

[0050] In the present invention, the STKX component is automatically called by a program to generate instead of manually operating the STK software. The designed rapid generation process of multi-satellite situation data and the classified processing process of report data take the parameters set in the configuration file as conditions and the orbit data as input. After "one-key start" calculation, the whole process requires no human intervention and no need to open the STK software. The software automatically calls the STKX component to complete a series of operations such as scene creation, satellite addition, and report calculation, realizing the full-process automation from orbit data to the generation of situation information and saving the time of operating the software.

[0051] 5. Classified Processing of Report Data

[0052] Two different orbit types, namely high-earth orbit and low-earth orbit, are distinguished, and the report data is processed separately. Based on the report data, secondary processing is carried out to judge the fixed-point or drifting state of high-earth orbit satellites and the orbit type of low-earth orbit satellites, obtaining more intuitive situation information.

[0053] 6. Comprehensive Display and Interaction of Situation Information

[0054] Utilizing the powerful interface design ability of QT and the 2D and 3D visualization functions of the STKX component, the visualization display of multi-satellite situation information is realized. While providing "one-key start" generation, interaction interfaces such as scene control, simulation control, and manual data import are also provided, facilitating users to adjust satellite parameters and understand the situation of multiple satellites.

[0055] 7. High Accuracy

[0056] Compared with the method of manually operating the STK software to generate, using the present invention can avoid problems such as misoperations and omissions in the processes of manually operating the STK software, manually screening data, and manually analyzing and processing data, with high accuracy. Taking 400 groups of orbit data as input and using the present invention to generate 400 groups of situation information, the calculation accuracy is 100%.

[0057] 8. Good Human-Machine Applicability

[0058] Through the high integration of the STKX component and the QT GUI, the complex operation logic of the STK software is transformed into an easy-to-understand and easy-to-operate custom GUI operation logic, enabling users to avoid facing the complex STK software interface and realizing the decoupling of users from the STK software. Non-professional users can also quickly get started.

[0059] 9. Strong Scalability

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

[0061] The present invention will be further described in detail below with reference to the drawings and embodiments.

[0062] Figure 1 It is a schematic flowchart of a method for quickly generating satellite situation information provided by the present invention.

[0063] Figure 2 It is a schematic diagram of the information interface when using the present invention for multi-satellite situation information calculation.

[0064] Figure 3 It is a schematic diagram of the graphical user interface of the QT third-party software designed by the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0065] As Figures 1-3 shown, the embodiment of the present invention provides a method for quickly generating satellite situation information, which is applicable to the automatic generation of 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 an interconnection relationship between QT and STK. As Figure 3 shown, a three-dimensional earth display and a two-dimensional map ActiveX control are embedded in the graphical user interface;

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

[0068] Step 3: Based on the Transmission Control Protocol (TCP), use the QT third-party software as the client to send a request for obtaining 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;

[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. AsFigure 3 As shown, it shows all the satellite orbits added to the STK scenario and displays the remaining fuel and orbital epoch time of all satellites in tabular form;

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

[0071] Through the LLA Position report, automatically filter out the orbital altitude at a specified moment in the target satellite orbit data, and obtain the drift rate and sub-satellite point longitude;

[0072] Through the Classical Orbit Element report, automatically filter out the orbital inclination at a specified moment in the target satellite orbit data;

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

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

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

[0076] In Step One, the method of embedding 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 2D display control of the STKX component in the system registry; through the setControl() function of the QAxWidget class in QT, embed the 3D display control and 2D display control of the STKX component into the graphical user interface of the QT third-party software; among them, 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, remaining fuel of the satellite, and / or custom text;

[0079] The configuration file includes: configuration file of the satellite to be added, configuration file of the rendezvous satellite, configuration file of the remaining fuel, and / or configuration file of custom text; where

[0080] The configuration file of the satellite to be added is divided into two types: imported in the form of six orbital elements and imported in the form of a TLE file, which is used to set the target satellite to be added to the STK scenario, and associate the satellite code or NORAD satellite number with the satellite name;

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

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

[0083] The configuration file of custom text 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, establishing the connection relationship between the QT third-party software and the satellite orbit database is implemented through the socket programming interface of the TCP protocol provided by the QtcpSocket class in QT. The relevant codes for sending data requests and reading data content are shown in Table 2:

[0089] Table 2

[0090]

[0091] In step 4, the STK scenario display forms include three-dimensional and two-dimensional, which are implemented through the display control controls in the STKX component, including three-dimensional scene display control control and two-dimensional scene display control control. 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.

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

[0093] In Step 5, the method of automatic screening is as follows: save the generated report in the form of a txt file locally, and read the data at the specified position in the txt file through the open() function provided by the QFile class in QT to achieve automatic screening of the data.

[0094] In Steps 4 and 5, the third-party software issues instructions through the ExecuteCommand() function provided by STKX. The command contents and formats for scenario creation, satellite addition, report generation, etc. 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, Classical Orbit Element report, and AER report to obtain the situation information of a single satellite includes:

[0099] Judge 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, judge whether the high-orbit satellite is in a fixed-point state or a drifting state based on the drift rate, and judge the drifting 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, calculate the height difference between the perigee and apogee of the low-orbit satellite. If the height difference is less than the threshold, it is determined that the low-orbit satellite is in a circular orbit, otherwise it is in an elliptical orbit.

[0101] In Step 6, the calculation method of the drift rate is as follows:

[0102] The high-orbit satellite operates in an orbit at a height of H kilometers from the geostationary orbit. The drift rate v p (degrees / day) is:

[0103]

[0104] where a0 is the semi-major axis of the geostationary orbit.

[0105] In Step 6, the method of judging whether the high-orbit satellite is in a fixed-point state or a drifting state based on the drift rate includes:

[0106] Affected by orbit perturbation, when |v pWhen it is less than 0.1 degree per day, it is determined that the high-orbit satellite is in a fixed-point state; otherwise, it is determined that the high-orbit satellite is in a drifting state. Among them, the fixed-point state of the high-orbit satellite means that at the same moment every day, the longitude change of the sub-satellite point of the high-orbit satellite is stable within the threshold range; the drifting state of the high-orbit satellite means that at the same moment every day, the longitude change of the sub-satellite point of the high-orbit satellite exceeds the threshold.

[0107] In step six, the method for judging the drifting direction of the high-orbit satellite includes:

[0108] When the orbital altitude of the high-orbit satellite is higher than the geostationary orbit altitude, H is positive, and v p is positive, indicating that the high-orbit satellite drifts 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 is negative, indicating that the high-orbit satellite drifts eastward relative to the geostationary orbit.

[0109] In the present invention, the STKX component is automatically called by the program to generate instead of manually operating the STK software to generate. The designed multi-satellite situation data rapid generation process and report data classification and processing process save the time of operating the software. It takes about 145 seconds to generate the situation information of 2 satellites by manually operating the STK software. The time-consuming of the main steps for generating the situation information of 2 satellites by manually operating the STK software is shown in Table 4.

[0110] Table 4

[0111]

[0112]

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

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

[0115] Taking the third-party application software designed by the present invention as an example, with the calculation of 15 high-orbit satellites, 15 low-orbit satellites, and 3 groups of rendezvous relationships, the description is as follows:

[0116] 1. Verification scenario setting

[0117] (1) Orbital elements

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

[0119] Table 5

[0120]

[0121]

[0122] The TLE elements of 5 high - orbit satellites and 5 low - orbit satellites are shown in Table 6 as follows:

[0123] Table 6

[0124]

[0125]

[0126]

[0127] (2) Simulation time

[0128] Beijing time: from 12:00:00 on August 11, 2024 to 12:00:00 on August 14, 2024.

[0129] (3) Configuration file settings

[0130] Modify the configuration files (six - element numbers) of the satellites to be added, the rendezvous satellite configuration file, the remaining fuel configuration file, and the custom text configuration file information respectively 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 duration is about 8 seconds, and the following situation information is obtained:

[0138] Satellite A01 (epoch time 2024 - 08 - 10 12:00:00.000) is fixed at the geosynchronous orbit, with an orbital altitude of about 35829.99 km, an orbital inclination of about 0.14 degrees, the sub - satellite point longitude 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] Satellite A02 (Epoch time: 2024-08-10 12:00:00.000) is currently approximately 100.12 kilometers below the geostationary orbit, with an orbital altitude of approximately 35730.04 kilometers. It drifts eastward at a rate of approximately 1.28 degrees per day, with an orbital inclination of approximately 0.14 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 59.45 degrees west longitude, and the remaining fuel is 458.02 kilograms (remaining fuel update time: 2023-08-09 12:00:00);

[0140] Satellite A03 (Epoch time: 2024-08-10 12:00:00.000) is fixed at the geostationary orbit, with an orbital altitude of approximately 35830.16 kilometers, an orbital inclination of approximately 15.00 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 34.90 degrees west longitude, and the remaining fuel is 123.56 kilograms (remaining fuel update time: 2023-08-05 20:00:00);

[0141] Satellite A04 (Epoch time: 2024-08-10 12:00:00.000) is currently approximately 99.76 kilometers above the geostationary orbit, with an orbital altitude of approximately 35888.67 kilometers. It drifts westward at a rate of approximately 1.28 degrees per day, with an orbital inclination of approximately 0.14 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 39.39 degrees west longitude, and the remaining fuel is 203.65 kilograms (remaining fuel update time: 2023-08-08 08:00:00);

[0142] Satellite A05 (Epoch time: 2024-08-10 12:00:00.000) is fixed at the geostationary orbit, with an orbital altitude of approximately 35781.92 kilometers, an orbital inclination of approximately 3.00 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 7.50 degrees west longitude, and the remaining fuel is 50.42 kilograms (remaining fuel update time: 2023-08-08 08:00:00);

[0143] Satellite A06 (Epoch time: 2024-08-10 12:00:00.000) is fixed at the geostationary orbit, with an orbital altitude of approximately 35788.39 kilometers, an orbital inclination of approximately 3.00 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 6.68 degrees west longitude, and the remaining fuel is 30.69 kilograms (remaining fuel update time: 2024-08-09 08:00:00);

[0144] Satellite A07 (epoch time: 2024-08-10 12:00:00.000) is fixed at the geosynchronous orbit, with an orbital altitude of approximately 35,787.89 km, an orbital inclination of approximately 0.14 degrees. At 12:00 on August 11th, the sub-satellite point longitude is approximately 23.98 degrees east longitude, and the remaining fuel is 45.68 kg (remaining fuel update time: 2024-08-09 08:00:00);

[0145] Satellite A08 (epoch time: 2024-08-10 12:00:00.000) is fixed at the geosynchronous orbit, with an orbital altitude of approximately 35,829.50 km, an orbital inclination of approximately 5.00 degrees. At 12:00 on August 11th, the sub-satellite point longitude is approximately 84.60 degrees east longitude, and the remaining fuel is 410.25 kg (remaining fuel update time: 2024-08-09 08:00:00);

[0146] Satellite A09 (epoch time: 2024-08-10 12:00:00.000) is fixed at the geosynchronous orbit, with an orbital altitude of approximately 35,788.13 km, an orbital inclination of approximately 0.14 degrees. At 12:00 on August 11th, the sub-satellite point longitude is approximately 115.58 degrees east longitude, and the remaining fuel is 326.05 kg (remaining fuel update time: 2024-08-09 08:00:00);

[0147] Satellite A10 (epoch time: 2024-08-10 12:00:00.000) is currently approximately 60.30 km below the geosynchronous orbit, with an orbital altitude of approximately 35,728.14 km, drifting eastward at a rate of approximately 0.77 degrees per day, an orbital inclination of approximately 0.14 degrees. At 12:00 on August 11th, the sub-satellite point longitude is approximately 149.66 degrees east longitude, and the remaining fuel is 453.01 kg (remaining fuel update time: 2024-08-09 08:00:00);

[0148] Satellite B01 (epoch time: 1967-10-29 08:00:00.000) is fixed at the geosynchronous orbit, with an orbital inclination of approximately 38.95 degrees. At 12:00 on August 11th, the sub-satellite point longitude is approximately 169.63 degrees west longitude, and the remaining fuel is 128.09 kg;

[0149] Satellite B02 (epoch time: 1967-10-29 08:00:00.000) is currently approximately 13.89 km above the geosynchronous orbit, with an orbital altitude of approximately 35,812.18 km, drifting westward at a rate of approximately 0.18 degrees per day, an orbital inclination of approximately 34.80 degrees. At 12:00 on August 11th, the sub-satellite point longitude is approximately 161.10 degrees west longitude, and the remaining fuel is 136.85 kg;

[0150] Satellite B03 (epoch time: 1967-10-29 08:00:00.000) is fixed in the geosynchronous orbit with an orbital inclination of approximately 23.17 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 134.31 degrees west longitude, and the remaining fuel is 203.47 kg;

[0151] Satellite B04 (epoch time: 1967-10-29 08:00:00.000) is fixed in the geosynchronous orbit with an orbital inclination of approximately 58.99 degrees. At 12:00 on August 11, the sub-satellite point longitude is approximately 149.28 degrees west longitude, and the remaining fuel is 845.02 kg;

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

[0153] Satellite C01 operates in a circular orbit with an orbital altitude of approximately 300 km, and the remaining fuel is 78.65 kg (remaining fuel update time: 2024-08-10 10:30:00);

[0154] Satellite C02 operates in a circular orbit with an orbital altitude of approximately 300 km, and the remaining fuel is 45.63 kg (remaining fuel update time: 2023-08-09 12:00:00);

[0155] Satellite C03 operates in a circular orbit with an orbital altitude of approximately 300 km, and the remaining fuel is 48.06 kg (remaining fuel update time: 2023-08-05 20:00:00);

[0156] Satellite C04 operates in a circular orbit with an orbital altitude of approximately 300 km, and the remaining fuel is 89.56 kg (remaining fuel update time: 2023-08-08 08:00:00);

[0157] Satellite C05 operates in a circular orbit with an orbital altitude of approximately 300 km, and the remaining fuel is 114.56 kg (remaining fuel update time: 2023-08-08 08:00:00);

[0158] Satellite C06 operates in a circular orbit with an orbital altitude of approximately 400 km, and the remaining fuel is 111.87 kg (remaining fuel update time: 2024-08-09 08:00:00);

[0159] Satellite C07 is operating in a circular orbit at an altitude of approximately 400 kilometers, with 52.06 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0160] Satellite C08 is operating in a circular orbit at an altitude of approximately 400 kilometers, with 41.75 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0161] Satellite C09 is operating in a circular orbit at an altitude of approximately 400 kilometers, with 136.52 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0162] Satellite C10 is operating in a circular orbit at an altitude of approximately 400 kilometers, with 135.23 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0163] Satellite D01 is operating in a circular orbit at an altitude of approximately 602 kilometers, with 85.02 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0164] Satellite D02 is operating in an elliptical orbit with a perigee of approximately 415 kilometers and an apogee of approximately 749 kilometers, with 74.03 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0165] Satellite D03 is operating in an elliptical orbit with a perigee of approximately 606 kilometers and an apogee of approximately 613 kilometers, with 41.63 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0166] Satellite D04 is operating in an elliptical orbit with a perigee of approximately 436 kilometers and an apogee of approximately 771 kilometers, with 45.85 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0167] Satellite D05 is operating in an elliptical orbit with a perigee of approximately 606 kilometers and an apogee of approximately 612 kilometers, with 50.86 kilograms of remaining fuel (remaining fuel update time: 2024-08-09 08:00:00);

[0168] At 12:00 on August 11, the distance between satellite A01 and satellite A03 was approximately 38,985.60 km. From 12:00 on August 11 to 12:00 on August 14, the moment of the closest distance between the two satellites was 2024-08-12 00:50:42.428, and the closest distance was approximately 38,829.73 km. At the moment of the closest distance, the sub-satellite point longitude of satellite A01 was approximately 89.78 degrees west longitude, and the sub-satellite point longitude of satellite A03 was approximately 35.18 degrees west longitude;

[0169] At 12:00 on August 11, the distance between satellite A06 and satellite B05 was approximately 56,674.70 km. From 12:00 on August 11 to 12:00 on August 14, the moment of the closest distance between the two satellites was 2024-08-11 16:49:08.602, and the closest distance was approximately 53,019.39 km. At the moment of the closest distance, the sub-satellite point longitude of satellite A06 was approximately 6.70 degrees west longitude, and the sub-satellite point longitude of satellite B05 was approximately 83.81 degrees west longitude;

[0170] At 12:00 on August 11, the distance between satellite B01 and satellite B02 was approximately 28,376.81 km. From 12:00 on August 11 to 12:00 on August 14, the moment of the closest distance between the two satellites was 2024-08-14 02:24:07.933, and the closest distance was approximately 12,038.15 km. At the moment of the closest distance, the sub-satellite point longitude of satellite B01 was approximately 177.15 degrees west longitude, and the sub-satellite point longitude of satellite B02 was approximately 159.81 degrees west longitude;

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

[0172] 3. Time-consuming statistics

[0173] It took approximately 10 seconds to generate the situation information of the above 30 satellites, which was only 0.46% of the time (about 36 minutes) required for manual operation of the STK software to generate the situation information of 30 satellites, achieving the effect of rapid generation of situation information.

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

[0175] 1. Integration of STKX component and QT GUI

[0176] The STKX component is highly integrated into the QT GUI in the form of an ActiveX control, realizing the organic combination of the powerful space mission analysis and visualization capabilities of STK and the GUI development capabilities of QT. Through QT, secondary development and function expansion of the STKX component functions are achieved, and the problem that it is difficult for users to decouple from the STK software is solved.

[0177] 2. Multi-type highly flexible configuration interfaces

[0178] Multiple types of configuration files are designed, and the formats of each type of configuration file are defined. Through a highly flexible configuration interface, the matching and association between satellite codes or NORAD satellite numbers and satellite names, as well as the matching and association between satellite names and remaining fuel information, are completed. It is configured as needed which satellites are added to the scenario and which rendezvous information between satellites is generated.

[0179] 3. Automatic Orbit Data Acquisition Interface

[0180] An efficient data interface based on the C / S architecture and TCP protocol is designed and implemented. This interface can connect QT to the orbit database. By means of the client sending orbit data acquisition requests, the server reading database data and returning orbit data, and the client receiving orbit data, it can obtain the required data 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 the STKX component to generate instead of manually operating the STK software. The designed rapid generation process of multi-satellite situation data and the classified processing process of report data take the parameters set by the configuration file as conditions and the orbit data as input. After "one-key start" calculation, the whole process requires no human intervention and no need to open the STK software. The software automatically calls the STKX component to complete a series of operations such as scenario creation, satellite addition, and report calculation, realizing the full-process automation from orbit data to situation information generation and saving the time of operating the software.

[0183] 5. Classified Processing of Report Data

[0184] Two different orbit types, high orbit and low orbit, are distinguished, and the report data is processed separately. On the basis of the report data, secondary processing is carried out to judge the fixed-point or drift state of high-orbit satellites and the orbit type of low-orbit satellites, obtaining more intuitive situation information.

[0185] 6. Comprehensive Display and Interaction of Situation Information

[0186] Utilizing the powerful interface design ability of QT and the 2D and 3D visualization functions of the STKX component, the visualization display of multi-satellite situation information is realized. While providing "one-key start" generation, it also provides interaction interfaces such as scenario control, simulation control, and manual data import, facilitating users to adjust satellite parameters and understand the situation of multiple satellites.

[0187] 7. High Accuracy

[0188] Compared with the method of manually operating the STK software to generate data, using the present invention can avoid problems such as misoperations and omissions during the processes of manually operating the STK software, manually screening data, and manually analyzing and processing data, with high accuracy. Taking 400 sets of orbital data as input and using the present invention to generate 400 sets of situation information, the calculation accuracy is 100%.

[0189] 8. Good human-machine applicability

[0190] Through the highly integrated STKX component and QT GUI, the complex operation logic of the STK software is transformed into an easy-to-understand and easy-to-operate custom GUI operation logic, enabling users to avoid facing the complex STK software interface and achieving the decoupling of the user and the STK software. Non-professional users can also quickly get started and use it.

[0191] 9. Strong scalability

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

[0193] As described above, the above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to 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 ActiveX controls, thereby establishing the 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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