A method for attitude guidance of spaceborne synthetic aperture radar satellite

Abstract

The present application discloses a satellite attitude guidance method for a spaceborne synthetic aperture radar, which relates to the field of satellite attitude guidance technology, and includes confirming a preset attitude angle corresponding to a target satellite facing a target imaging area based on the real-time orbit information of the target satellite and a predetermined imaging mission plan; using a preset monitoring device to monitor the current attitude angle corresponding to the target satellite in real time, and then confirming the attitude deviation coefficient corresponding to the target satellite; according to the attitude deviation coefficient corresponding to the target satellite, starting an attitude adjustment module to guide the attitude of the target satellite. The present application has the effect of improving the satellite attitude guidance effect.

Description

Technical Field

[0001] This application relates to the field of satellite attitude guidance technology, and in particular to a satellite attitude guidance method for spaceborne synthetic aperture radar. Background Technology

[0002] Synthetic Aperture Radar (SAR) is a high-resolution imaging radar that can obtain high-resolution radar images similar to optical photography under extremely low visibility weather conditions. It utilizes the relative motion between the radar and the target to synthesize a larger equivalent antenna aperture from smaller real antenna apertures through data processing; this is also called synthetic aperture radar. The characteristics of synthetic aperture radar are high resolution, all-weather operation, and effective identification of camouflage and penetration of concealment. The resulting high azimuth resolution is equivalent to that provided by a large-aperture antenna.

[0003] In related technologies, existing satellite attitude guidance methods do not analyze satellite data from multiple angles, resulting in significant deviations in the corresponding satellite attitude angles, which needs improvement. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this application provides a satellite attitude guidance method for spaceborne synthetic aperture radar.

[0005] Firstly, this application provides a satellite attitude guidance method for spaceborne synthetic aperture radar, employing the following technical solution:

[0006] A satellite attitude guidance method for spaceborne synthetic aperture radar includes the following steps:

[0007] Based on the real-time orbital information of the target satellite and the predetermined imaging mission plan, the preset attitude angle corresponding to the target satellite facing the target imaging area is confirmed.

[0008] The current attitude angle of the target satellite is monitored in real time using a preset monitoring device, thereby confirming the attitude deviation coefficient of the target satellite.

[0009] Based on the attitude deviation coefficient corresponding to the target satellite, the attitude adjustment module is activated to guide the attitude of the target satellite.

[0010] By adopting the above technical solution, the preset attitude angle corresponding to the target satellite facing the target imaging area is confirmed, and the current attitude angle of the target satellite is monitored in real time by the monitoring device. The attitude deviation coefficient of the target satellite is confirmed, and then the attitude of the target satellite is guided based on the attitude deviation coefficient of the target satellite, thereby effectively improving the attitude guidance effect of the target satellite.

[0011] Preferably, confirming the preset attitude angle corresponding to when the target satellite faces the target imaging area specifically includes:

[0012] The real-time orbital information of the target satellite is collected based on the preset receiving device, and the geographical coordinates corresponding to the target imaging area are confirmed based on the predetermined imaging mission plan.

[0013] Using the orbit prediction model, the time points corresponding to the target imaging area when the target satellite passes over are calculated;

[0014] Then, based on the real-time orbit information of the satellite and the geographical coordinates of the target imaging area, the preset attitude angle of the target satellite at the time node is confirmed. The preset attitude angle includes a preset yaw angle, a preset pitch angle and a preset roll angle.

[0015] Preferably, confirming the attitude deviation coefficient corresponding to the target satellite specifically includes:

[0016] The current attitude angle of the target satellite is monitored in real time by a monitoring device, and the current yaw angle of the target satellite is extracted from the current attitude angle. Current pitch angle and current roll angle ;

[0017] Through calculation formula The attitude deviation coefficient of the target satellite is obtained. ,in, This is represented by the preset yaw angle, preset pitch angle, and preset roll angle corresponding to the target satellite. This is represented by the preset permissible yaw angle difference, permissible pitch angle difference, and permissible roll angle difference. This is represented by the preset weighting coefficient.

[0018] Preferably, the attitude guidance for the target satellite specifically includes:

[0019] The attitude deviation coefficient corresponding to the target satellite With respect to the preset attitude deviation threshold range A comparison was conducted, in which, This is represented by the preset first attitude deviation threshold. This is represented as a preset second attitude deviation threshold;

[0020] If the attitude deviation coefficient of the target satellite Therefore, there is no need to guide the attitude of the target satellite;

[0021] If the attitude deviation coefficient of the target satellite In If the situation is in between, further analysis is required;

[0022] If the attitude deviation coefficient of the target satellite Then, the attitude of the target satellite is guided based on the first correction coefficient.

[0023] The preferred further analysis process specifically includes:

[0024] Collect environmental information corresponding to the operation of the target satellite, analyze the environmental information, and confirm the environmental impact coefficient corresponding to the operation of the target satellite. ;

[0025] Identify the key nodes corresponding to the target satellite and obtain the runtime of each key node. Wear assessment coefficients corresponding to each key node ,in, This is represented by the number corresponding to each key node;

[0026] Through calculation formula The wear impact coefficient corresponding to the target satellite during operation was confirmed. ,in, Represented as the preset first The standard runtime for each key node. Represented as the preset first Standard wear assessment coefficients corresponding to each key node This is represented by the preset weighting coefficient, where e is the natural constant;

[0027] Through formula The second correction factor corresponding to the target satellite's operation was confirmed. Then, based on the second correction coefficient corresponding to the target satellite's operation, guidance is provided for the target satellite, wherein... This is represented by the preset weighting coefficient.

[0028] Preferably, the attitude guidance of the target satellite based on the first correction coefficient specifically includes:

[0029] Select a time window, obtain the attitude deviation coefficients corresponding to each time node, divide the time intervals, and determine the average attitude deviation coefficients corresponding to each time interval to form a time series. Then, apply a function to the average attitude deviation coefficients according to the time series. express;

[0030] Through the model The first correction factor corresponding to the target satellite's operation is obtained. ,in, This is expressed as the time interval between the attitude deviation coefficient and the first attitude deviation threshold. This represents the time interval during which the attitude deviation coefficient is greater than the second attitude deviation threshold.

[0031] Preferably, the wear and tear impact coefficient corresponding to the target satellite during operation is determined, which specifically includes:

[0032] The wear impact coefficient of the target satellite during operation is collected in real time, and a real-time variation curve of the wear impact coefficient of the target satellite is established. ;

[0033] Through formula The risk variation coefficient corresponding to the target satellite was identified. ,in, This is expressed as a proportionality coefficient. These represent the maximum and minimum wear impact coefficients corresponding to the target satellite during operation, respectively.

[0034] Risk change coefficient corresponding to the target satellite Compared with the preset risk change threshold Perform a comparison;

[0035] If the risk change coefficient corresponding to the target satellite This indicates that the risk value of each key node of the target satellite will increase in the future, and monitoring and early warning of each key node are required.

[0036] Secondly, this application provides a spaceborne synthetic aperture radar satellite attitude guidance system, which adopts the following technical solution:

[0037] A spaceborne synthetic aperture radar satellite attitude guidance system includes:

[0038] The information analysis module is used to determine the preset attitude angle of the target satellite when it faces the target imaging area, based on the real-time orbit information of the target satellite and the predetermined imaging mission plan.

[0039] The information acquisition module is used to monitor the current attitude angle of the target satellite in real time using a preset monitoring device, and then confirm the attitude deviation coefficient of the target satellite.

[0040] The attitude adjustment module is used to guide the attitude of the target satellite by activating the attitude adjustment module according to the attitude deviation coefficient corresponding to the target satellite.

[0041] Thirdly, this application provides a computer-readable storage medium storing instructions that, when executed on a computer, cause the computer to perform any of the above-described methods for attitude guidance of a spaceborne synthetic aperture radar satellite.

[0042] In summary, this application includes at least one of the following beneficial technical effects:

[0043] 1. This invention provides a satellite attitude guidance method for spaceborne synthetic aperture radar. By confirming the preset attitude angle corresponding to the target satellite when facing the target imaging area, and by monitoring the current attitude angle of the target satellite in real time through a monitoring device, the attitude deviation coefficient of the target satellite is confirmed, and then the attitude of the target satellite is guided based on the attitude deviation coefficient of the target satellite, thereby effectively improving the attitude guidance effect of the target satellite.

[0044] 2. By analyzing the environmental information and operational status of the target satellite during operation, the environmental impact coefficient and wear impact coefficient of the target satellite during operation are confirmed. The second correction coefficient of the target satellite during operation is further confirmed, and the target satellite is guided based on the second correction coefficient, thereby effectively improving the attitude guidance effect of the target satellite. Attached Figure Description

[0045] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0046] Figure 1 This is a flowchart of a satellite attitude guidance method for a spaceborne synthetic aperture radar according to an embodiment of this application.

[0047] Figure 2 This is a schematic diagram of a satellite attitude guidance system for a spaceborne synthetic aperture radar according to an embodiment of this application. Detailed Implementation

[0048] The following is in conjunction with the appendix Figure 1-2 This application will be described in further detail.

[0049] Example 1

[0050] This application discloses a satellite attitude guidance method for spaceborne synthetic aperture radar.

[0051] Reference Figure 1 A satellite attitude guidance method for spaceborne synthetic aperture radar includes the following steps:

[0052] S1. Based on the real-time orbital information of the target satellite and the predetermined imaging mission plan, confirm the preset attitude angle corresponding to the target satellite facing the target imaging area;

[0053] S2. Use a preset monitoring device to monitor the current attitude angle of the target satellite in real time, and then confirm the attitude deviation coefficient of the target satellite;

[0054] S3. Based on the attitude deviation coefficient corresponding to the target satellite, activate the attitude adjustment module to guide the attitude of the target satellite.

[0055] Furthermore, confirming the preset attitude angle corresponding to the target satellite facing the target imaging area specifically includes:

[0056] The real-time orbital information of the target satellite is collected based on the preset receiving device, and the geographical coordinates corresponding to the target imaging area are confirmed based on the predetermined imaging mission plan.

[0057] Using the orbit prediction model, the time points corresponding to the target imaging area when the target satellite passes over are calculated;

[0058] Then, based on the real-time orbit information of the satellite and the geographical coordinates of the target imaging area, the preset attitude angle of the target satellite at the time node is confirmed. The preset attitude angle includes a preset yaw angle, a preset pitch angle and a preset roll angle.

[0059] Specifically, the satellite orbit information is confirmed using Kepler orbital elements or state vectors, the geographic coordinates corresponding to the target imaging area are converted into position vectors in the geocentric and geofixed coordinate system, and the position and velocity vectors of the target satellite in the inertial coordinate system are confirmed at the time node corresponding to the target satellite passing over the target imaging area. The position and velocity vectors are further converted from the inertial coordinate system to the geocentric and geofixed coordinate system, thereby confirming the preset attitude angle corresponding to the target satellite facing the target imaging area.

[0060] It should be noted that confirming the attitude deviation coefficient corresponding to the target satellite specifically includes:

[0061] The current attitude angle of the target satellite is monitored in real time by a monitoring device, and the current yaw angle of the target satellite is extracted from the current attitude angle. Current pitch angle and current roll angle ;

[0062] Through calculation formula The attitude deviation coefficient of the target satellite is obtained. ,in, This is represented by the preset yaw angle, preset pitch angle, and preset roll angle corresponding to the target satellite. This is represented by the preset permissible yaw angle difference, permissible pitch angle difference, and permissible roll angle difference. This is represented by the preset weighting coefficient.

[0063] Furthermore, the attitude of the target satellite is guided, specifically including:

[0064] The attitude deviation coefficient corresponding to the target satellite With respect to the preset attitude deviation threshold range A comparison was conducted, in which, This is represented by the preset first attitude deviation threshold. This is represented as a preset second attitude deviation threshold;

[0065] If the attitude deviation coefficient of the target satellite Therefore, there is no need to guide the attitude of the target satellite;

[0066] If the attitude deviation coefficient of the target satellite In If the situation is in between, further analysis is required;

[0067] If the attitude deviation coefficient of the target satellite Then, the attitude of the target satellite is guided based on the first correction coefficient.

[0068] Specifically, by comparing the attitude deviation coefficient of the target satellite with the preset attitude deviation threshold range, the attitude deviation threshold range in which the attitude deviation coefficient of the target satellite falls is confirmed, and analysis and processing are performed according to different attitude deviation threshold ranges, thereby effectively improving the attitude guidance effect of the target satellite.

[0069] It should be noted that the further analysis process specifically includes:

[0070] Collect environmental information corresponding to the operation of the target satellite, analyze the environmental information, and confirm the environmental impact coefficient corresponding to the operation of the target satellite. ;

[0071] Specifically, the environmental impact factors corresponding to the operation of the target satellite are identified, including but not limited to solar radiation pressure, ground-based radiation pressure, and solar drag. The environmental impact coefficients corresponding to each environmental impact factor are extracted from the cloud database, and the environmental impact coefficients corresponding to the operation of the target satellite are determined by averaging.

[0072] Identify the key nodes corresponding to the target satellite and obtain the runtime of each key node. Wear assessment coefficients corresponding to each key node ,in, This is represented by the number corresponding to each key node;

[0073] Specifically, during the operation of the target satellite, over time, mechanical components on the target satellite (such as reaction wheels, gyroscopes, etc.) may wear down, affecting the performance of the target satellite. Therefore, it is necessary to monitor the key nodes of the target satellite and determine the operating time and wear assessment coefficient of each key node.

[0074] Through calculation formula The wear impact coefficient corresponding to the target satellite during operation was confirmed. ,in, Represented as the preset first The standard runtime for each key node. Represented as the preset first Standard wear assessment coefficients corresponding to each key node This is represented by the preset weighting coefficient, where e is the natural constant;

[0075] Through formula The second correction factor corresponding to the target satellite's operation was confirmed. Then, based on the second correction coefficient corresponding to the target satellite's operation, guidance is provided for the target satellite, wherein... This is represented by the preset weighting coefficient.

[0076] Specifically, by analyzing the environmental information and operational status of the target satellite during operation, the environmental impact coefficient and wear impact coefficient of the target satellite during operation are confirmed. The second correction coefficient of the target satellite during operation is further confirmed, and the target satellite is guided based on the second correction coefficient, thereby effectively improving the attitude guidance effect of the target satellite.

[0077] Furthermore, the attitude of the target satellite is guided based on the first correction coefficient, specifically including:

[0078] Select a time window, obtain the attitude deviation coefficients corresponding to each time node, divide the time intervals, and determine the average attitude deviation coefficients corresponding to each time interval to form a time series. Then, apply a function to the average attitude deviation coefficients according to the time series. express;

[0079] Through the model The first correction factor corresponding to the target satellite's operation is obtained. ,in, This is expressed as the time interval between the attitude deviation coefficient and the first attitude deviation threshold. This represents the time interval during which the attitude deviation coefficient is greater than the second attitude deviation threshold.

[0080] It should be noted that confirming the wear and tear impact coefficient corresponding to the target satellite's operation also includes:

[0081] The wear impact coefficient of the target satellite during operation is collected in real time, and a real-time variation curve of the wear impact coefficient of the target satellite is established. ;

[0082] Through formula The risk variation coefficient corresponding to the target satellite was identified. ,in, This is expressed as a proportionality coefficient. These represent the maximum and minimum wear impact coefficients corresponding to the target satellite during operation, respectively.

[0083] Risk change coefficient corresponding to the target satellite Compared with the preset risk change threshold Perform a comparison;

[0084] If the risk change coefficient corresponding to the target satellite This indicates that the risk value of each key node of the target satellite will increase in the future, and monitoring and early warning of each key node are required.

[0085] Specifically, if the risk change coefficient corresponding to the target satellite If the risk value of each key node of the target satellite does not increase in the future, then there is no need to monitor and warn of each key node.

[0086] Example 2

[0087] This application also discloses a spaceborne synthetic aperture radar satellite attitude guidance system.

[0088] Reference Figure 2 A spaceborne synthetic aperture radar satellite attitude guidance system, comprising:

[0089] The information analysis module is used to determine the preset attitude angle of the target satellite when it faces the target imaging area, based on the real-time orbit information of the target satellite and the predetermined imaging mission plan.

[0090] The information acquisition module is used to monitor the current attitude angle of the target satellite in real time using a preset monitoring device, and then confirm the attitude deviation coefficient of the target satellite.

[0091] The attitude adjustment module is used to guide the attitude of the target satellite by activating the attitude adjustment module according to the attitude deviation coefficient corresponding to the target satellite.

[0092] The above description is merely an example and illustration of the concept of the present invention. Those skilled in the art can make various modifications or additions to the specific embodiments described or use similar methods to replace them, as long as they do not deviate from the concept of the invention or exceed the scope defined in the claims, they should all fall within the protection scope of the present invention.

[0093] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0094] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to specific implementations. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A method for satellite attitude guidance of a spaceborne synthetic aperture radar, characterized in that: The following steps are involved: Based on the real-time orbit information of the target satellite and the predetermined imaging mission plan, determining a preset attitude angle corresponding to the target satellite when facing the target imaging area; Using a preset monitoring device to monitor the current attitude angle corresponding to the target satellite in real time, and then confirming the attitude deviation coefficient corresponding to the target satellite; According to the attitude deviation coefficient corresponding to the target satellite, an attitude adjustment module is started to guide the attitude of the target satellite; Guiding the attitude of the target satellite specifically includes: The attitude deviation coefficient corresponding to the target satellite The deviation threshold from the preset posture For comparison, Represented as the preset first posture deviation threshold, Represented as a preset second posture deviation threshold; If the attitude deviation coefficient corresponding to the target satellite , then there is no need to guide the attitude of the target satellite; If the attitude deviation coefficient corresponding to the target satellite In If the number is between , further analysis is required; If the attitude deviation coefficient corresponding to the target satellite , guiding the attitude of the target satellite based on the first correction coefficient; The further analysis process includes: Collect the corresponding environmental information when the target satellite is running, analyze the environmental information, and confirm the corresponding environmental impact coefficient when the target satellite is running ; Confirm the key nodes corresponding to the target satellite and obtain the running time corresponding to each key node of the target satellite And the wear assessment coefficient corresponding to each key node ,in, It is represented by the number corresponding to each key node; By calculating the formula , confirm the corresponding wear influence coefficient of the target satellite during operation ,in, Indicated as the preset The standard running time corresponding to each key node is: Indicated as the preset The standard wear assessment coefficient corresponding to each key node is: It is expressed as a preset weight coefficient, and e is a natural constant; By formula , confirm the second correction coefficient corresponding to the target satellite's operation , and then guide the target satellite based on the second correction coefficient corresponding to the target satellite during its operation, wherein, Represented as a preset weight coefficient.

2. The method for satellite-borne synthetic aperture radar attitude guidance according to claim 1, characterized in that: Confirming the preset attitude angle corresponding to the target satellite facing the target imaging area specifically includes: Collecting the real-time orbit information of the target satellite based on a preset receiving device, and confirming the geographic coordinates corresponding to the target imaging area based on a predetermined imaging mission plan; Using the orbit prediction model, the time node corresponding to the target satellite passing through the target imaging area is calculated; Then, according to the real-time orbit information corresponding to the satellite and the geographic coordinates corresponding to the target imaging area, the preset attitude angle corresponding to the target satellite at the time node is confirmed, and the preset attitude angle includes a preset yaw angle, a preset pitch angle and a preset roll angle.

3. The method for satellite-borne synthetic aperture radar attitude guidance according to claim 2, characterized in that: Confirming the attitude deviation coefficient corresponding to the target satellite, specifically including: The current attitude angle corresponding to the target satellite is monitored in real time by a monitoring device, and the current yaw angle corresponding to the target satellite is extracted from the current attitude angle corresponding to the target satellite. , Current pitch angle and the current roll angle ; By calculating the formula , and obtain the attitude deviation coefficient corresponding to the target satellite ,in, It is represented by the preset yaw angle, preset pitch angle, and preset roll angle corresponding to the target satellite. It is expressed as the preset permissible yaw angle difference, permissible pitch angle difference, and permissible roll angle difference. Represented as a preset weight coefficient.

4. The method for satellite-borne synthetic aperture radar attitude guidance according to claim 3, characterized in that: Guiding the attitude of the target satellite based on the first correction coefficient specifically includes: Select a time window, obtain the attitude deviation coefficient corresponding to each time node, divide the time interval, and confirm the mean of the attitude deviation coefficient corresponding to each time interval to form a time series, and use the function to calculate the mean of the attitude deviation coefficient according to the time series. express; By Model , and obtain the first correction coefficient corresponding to the target satellite's operation ,in, It is expressed as the time interval between the first attitude deviation threshold and the second attitude deviation threshold, It is expressed as the time interval during which the posture deviation coefficient is greater than the second posture deviation threshold.

5. The method for satellite-borne synthetic aperture radar attitude guidance according to claim 4, characterized in that: Confirm the wear and tear coefficient of the target satellite during operation, including: Collect the wear influence coefficient of the target satellite in real time, and establish the real-time change curve of the wear influence coefficient of the target satellite ; By formula , confirm the risk change coefficient corresponding to the target satellite ,in, Expressed as a proportionality coefficient, They are respectively represented as the maximum wear influence coefficient and the minimum wear influence coefficient corresponding to the operation of the target satellite; The risk change coefficient corresponding to the target satellite Compared with the preset risk change threshold Make a comparison; If the risk change coefficient corresponding to the target satellite , it means that the risk value of each key node of the target satellite will increase in the future, and each key node needs to be monitored and warned.

6. A spaceborne synthetic aperture radar satellite attitude guidance system, characterized in that: include: An information analysis module, used to confirm a preset attitude angle corresponding to the target satellite when facing the target imaging area based on the real-time orbit information of the target satellite and the predetermined imaging mission plan; An information acquisition module is used to monitor the current attitude angle corresponding to the target satellite in real time using a preset monitoring device, and then confirm the attitude deviation coefficient corresponding to the target satellite; An attitude adjustment module, used to start the attitude adjustment module according to the attitude deviation coefficient corresponding to the target satellite, and guide the attitude of the target satellite; Guiding the attitude of the target satellite specifically includes: The attitude deviation coefficient corresponding to the target satellite The deviation threshold from the preset posture For comparison, Represented as the preset first posture deviation threshold, Represented as a preset second posture deviation threshold; If the attitude deviation coefficient corresponding to the target satellite , then there is no need to guide the attitude of the target satellite; If the attitude deviation coefficient corresponding to the target satellite In If the number is between , further analysis is required; If the attitude deviation coefficient corresponding to the target satellite , guiding the attitude of the target satellite based on the first correction coefficient; The further analysis process includes: Collect the corresponding environmental information when the target satellite is running, analyze the environmental information, and confirm the corresponding environmental impact coefficient when the target satellite is running ; Confirm the key nodes corresponding to the target satellite and obtain the running time corresponding to each key node of the target satellite And the wear assessment coefficient corresponding to each key node ,in, It is represented by the number corresponding to each key node; By calculating the formula , confirm the corresponding wear influence coefficient of the target satellite during operation ,in, Indicated as the preset The standard running time corresponding to each key node is: Indicated as the preset The standard wear assessment coefficient corresponding to each key node is: It is expressed as a preset weight coefficient, and e is a natural constant; By formula , confirm the second correction coefficient corresponding to the target satellite's operation , and then guide the target satellite based on the second correction coefficient corresponding to the target satellite during its operation, wherein, Represented as a preset weight coefficient.

7. A computer-readable storage medium, characterized in that: Instructions are stored, and when the instructions are executed on a computer, the computer is caused to execute a spaceborne synthetic aperture radar satellite attitude guidance method as claimed in any one of claims 1 to 5.

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