Satellite image shooting method, device, electronic device and computer readable medium

Abstract

This disclosure discloses satellite image acquisition methods, apparatus, electronic devices, and computer-readable media. One specific implementation of the method includes: acquiring satellite imaging position information; in response to determining that the error of the image position coordinates in the satellite imaging position information is greater than a preset position error threshold, performing the following satellite imaging fault troubleshooting steps: performing mission consistency detection on the imaging timestamp; performing satellite attitude anomaly detection on the satellite attitude data at the imaging time; performing orbit prediction verification on the satellite to generate a satellite orbit prediction error; in response to determining that the satellite orbit prediction error is greater than a preset orbit error threshold, performing time point verification on the satellite to generate time point verification information; generating a satellite imaging error result; based on the satellite imaging error result, performing fault adjustment on the satellite; and using the adjusted satellite to re-acquire images. This implementation can reduce the consumption of satellite imaging resources.

Description

Technical Field

[0001] Embodiments of the present disclosure relate to the field of computer technology, and in particular to a satellite image shooting method, device, electronic device, and computer-readable medium. Background Art

[0002] With the development of technology, the accuracy requirements for satellite imagery are getting higher and higher. At present, when shooting satellite images, the usual method is to manually determine whether the images taken by the satellite meet the requirements. Then, if an image that does not meet the requirements is found, each type of data in the image and the satellite-shot data (for example, satellite orbit coordinates, imaging mission coordinates, shooting angle, etc.) is checked separately to determine the cause of the abnormal shooting. This instructs the satellite to make adjustments to improve the shooting accuracy.

[0003] However, in practice, it is found that when using the above method to take satellite images, the following technical problems often occur:

[0004] First, the transit time of satellite photography is short, and remote adjustment requires repeated communication with the satellite through the ground station, and it is difficult to adjust to the appropriate level in time. As a result, it is easy to miss the opportunity to shoot satellites, thus wasting satellite photography resources;

[0005] Second, only each type of data is analyzed during the inspection process, and the analysis dimension is relatively single. However, satellite imaging errors may come from a variety of factors, such as orbit prediction errors, satellite attitude control anomalies, camera anomalies, etc. It is difficult to make judgments based on data information from multiple dimensions, which may lead to single-minded thinking on complex problems and difficulty in solving the problems comprehensively. As a result, it is difficult for the satellite to capture images more accurately after adjustment.

[0006] The above information disclosed in this Background section is only for enhancement of understanding of the background of the inventive concept and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art. Summary of the invention

[0007] The content of this disclosure is used to introduce concepts in a brief form, which will be described in detail in the detailed implementation section below. The content of this disclosure is not intended to identify the key features or essential features of the technical solution claimed for protection, nor is it intended to limit the scope of the technical solution claimed for protection.

[0008] Some embodiments of the present disclosure propose satellite image shooting methods, devices, electronic devices, and computer-readable media to solve one or more of the technical problems mentioned in the above background technology section.

[0009] In a first aspect, some embodiments of the present disclosure provide a satellite image shooting method, the method comprising: acquiring satellite imaging position information, wherein the satellite imaging position information comprises: image position coordinates, an imaging timestamp and satellite attitude data at the imaging moment; in response to determining that the error of the image position coordinates in the above satellite imaging position information is greater than a preset position error threshold, performing the following satellite imaging troubleshooting steps: performing task consistency detection on the above imaging timestamp to generate satellite camera startup fault information; performing satellite attitude anomaly detection on the above satellite attitude data at the imaging moment to generate satellite attitude anomaly information; based on the above satellite imaging moment and image position coordinates, performing orbit prediction verification on the above satellite to generate a satellite orbit prediction error; in response to determining that the above satellite orbit prediction error is greater than the preset orbit error threshold, performing time point verification on the above satellite to generate time point verification information; generating a satellite imaging error result based on the above satellite camera startup fault information, the above satellite attitude anomaly information, the above satellite orbit prediction error and the above time point verification information; based on the above satellite imaging error result, performing fault adjustment on the above satellite, and using the adjusted satellite to shoot images again.

[0010] In a second aspect, some embodiments of the present disclosure provide a satellite image shooting device, the device comprising: an acquisition unit, configured to acquire satellite imaging position information, wherein the satellite imaging position information comprises: image position coordinates, an imaging timestamp, and satellite attitude data at the imaging moment; a troubleshooting unit, configured to, in response to determining that an error in the image position coordinates in the above satellite imaging position information is greater than a preset position error threshold, perform the following satellite imaging troubleshooting steps: perform task consistency detection on the above imaging timestamp to generate satellite camera startup fault information; perform satellite attitude anomaly detection on the satellite attitude data at the imaging moment to generate satellite attitude anomaly detection; information; based on the satellite imaging time and image position coordinates, performing orbit prediction verification on the satellite to generate a satellite orbit prediction error; in response to determining that the satellite orbit prediction error is greater than a preset orbit error threshold, performing a time point verification on the satellite to generate time point verification information; a generating unit is configured to generate a satellite imaging error result based on the satellite camera startup fault information, the satellite attitude abnormality information, the satellite orbit prediction error and the time point verification information; an adjusting and shooting unit is configured to perform fault adjustment on the satellite based on the satellite imaging error result, and use the adjusted satellite to shoot images again.

[0011] In a third aspect, some embodiments of the present disclosure provide an electronic device comprising: one or more processors; a storage device on which one or more programs are stored, and when the one or more programs are executed by the one or more processors, the one or more processors implement the method described in any implementation manner of the above-mentioned first aspect.

[0012] In a fourth aspect, some embodiments of the present disclosure provide a computer-readable medium having a computer program stored thereon, wherein when the program is executed by a processor, the method described in any implementation manner of the above-mentioned first aspect is implemented.

[0013] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the satellite image shooting method of some embodiments of the present disclosure, the consumption of satellite shooting resources can be reduced. Specifically, the reason for wasting satellite shooting resources is that the transit time of satellite shooting is short, and remote adjustment requires repeated communication with the satellite through the ground station, and it is difficult to adjust to the appropriate degree in time. As a result, it is easy to miss the opportunity to shoot satellites. Based on this, the satellite image shooting method of some embodiments of the present disclosure first obtains satellite imaging position information. Among them, the satellite imaging position information includes: image position coordinates, imaging timestamp and satellite attitude data at the imaging moment. Then, in response to determining that the error of the image position coordinates in the above satellite imaging position information is greater than the preset position error threshold, the following satellite imaging troubleshooting steps are performed: the above imaging timestamp is subjected to task consistency detection to generate satellite camera startup fault information. The satellite attitude data at the above imaging moment is subjected to satellite attitude anomaly detection to generate satellite attitude anomaly information. Based on the above satellite imaging moment and image position coordinates, the above satellite is subjected to orbit prediction verification to generate a satellite orbit prediction error. In response to determining that the satellite orbit prediction error is greater than the preset orbit error threshold, the satellite is checked at a time point to generate time point verification information. Considering that the ground station adjustment requires communication and it is difficult to control the adjustment strength, in order to avoid missing the satellite transit time, by setting task consistency detection, satellite attitude anomaly detection, orbit prediction verification and time point verification, satellite fault troubleshooting can be automatically performed. Thus, the time to determine the fault problem is shortened. At the same time, troubleshooting in a multi-dimensional parallel manner can not only shorten the time to determine the fault, but also locate the fault problem from multiple dimensions, so as to facilitate targeted satellite adjustment. Then, based on the satellite camera startup fault information, the satellite attitude anomaly information, the satellite orbit prediction error and the time point verification information, a satellite imaging error result is generated. Thus, it can be used to locate the fault problem of satellite shooting. Finally, based on the satellite imaging error result, the satellite is adjusted for the fault, and the adjusted satellite is used to shoot the image again. Thus, the efficiency of fault adjustment can be greatly improved to avoid missing the satellite transit time. Then, the consumption of satellite shooting resources is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The above and other features, advantages and aspects of the embodiments of the present disclosure will become more apparent with reference to the following detailed description in conjunction with the accompanying drawings. Throughout the accompanying drawings, the same or similar reference numerals represent the same or similar elements. It should be understood that the drawings are schematic and that components and elements are not necessarily drawn to scale.

[0015] Figure 1 is a flow chart of some embodiments of the satellite image capturing method according to the present disclosure;

[0016] Figure 2 is a schematic structural diagram of some embodiments of the satellite image capturing device according to the present disclosure;

[0017] Figure 3 It is a schematic diagram of the structure of an electronic device suitable for implementing some embodiments of the present disclosure. DETAILED DESCRIPTION

[0018] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments set forth herein. On the contrary, these embodiments are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0019] It should also be noted that, for ease of description, only the parts related to the invention are shown in the drawings. In the absence of conflict, the embodiments and features in the embodiments of the present disclosure can be combined with each other.

[0020] It should be noted that the concepts such as "first" and "second" mentioned in the present disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0021] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0022] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0023] The present disclosure will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0024] Figure 1The process 100 of some embodiments of the satellite image shooting method according to the present disclosure is shown. The satellite image shooting method comprises the following steps:

[0025] Step 101, obtaining satellite imaging position information.

[0026] In some embodiments, the execution subject of the satellite image shooting method can obtain satellite imaging position information by wired or wireless means. The satellite imaging position information may include: image position coordinates, imaging timestamp, and satellite attitude data at the imaging time. The image position coordinates may be the coordinates when the satellite shoots the image. The satellite imaging image coordinates may be three-dimensional coordinates. The satellite attitude data at the imaging time may be the attitude data of the satellite camera when the satellite shoots the image. For example, it may include the pitch angle of the satellite camera at the imaging time, the roll angle at the imaging time, and the yaw angle at the imaging time.

[0027] It should be noted that the above wireless connection methods may include but are not limited to 3G / 4G connection, WiFi connection, Bluetooth connection, WiMAX connection, Zigbee connection, UWB (ultra wideband) connection, and other wireless connection methods currently known or to be developed in the future.

[0028] Optionally, before responding to determining that the image position coordinate error in the satellite imaging position information is greater than a preset position error threshold, the execution subject may further include the following steps:

[0029] The first step is to obtain the ground coordinates of the imaging mission.

[0030] In the second step, the latitude and longitude errors between the image position coordinates and the imaging task ground coordinates are determined as image position coordinate errors. The image position coordinate errors may be the relative distances between the image position coordinates and the predicted satellite imaging coordinates. Here, the predicted satellite imaging coordinates may be satellite shooting coordinates pre-calculated based on the satellite orbit and the imaging task ground coordinates.

[0031] Step 102, in response to determining that the error of the image position coordinates in the satellite imaging position information is greater than a preset position error threshold, performing the following satellite imaging troubleshooting steps:

[0032] Step 1021, performing task consistency detection on the imaging timestamp to generate satellite camera startup fault information.

[0033] In some embodiments, the execution subject may perform task consistency detection on the imaging timestamp in various ways to generate satellite camera startup failure information. The satellite camera startup failure information may be used to characterize whether the satellite camera has a startup failure. Secondly, the error of the image position coordinates may be the image position coordinate error.

[0034] In some optional implementations of some embodiments, the execution subject performs task consistency detection on the imaging timestamp to generate satellite camera startup fault information, which may include the following steps:

[0035] The first step is to obtain the task planning time point of the satellite imaging task. The task planning time point may be a time point of the shooting task set in advance. The task planning time point may be pre-estimated according to the imaging task.

[0036] In the second step, the time difference between the imaging timestamp and the mission planning time point is determined as the mission consistency time difference. The time difference between the imaging timestamp and the mission planning time point can represent the time difference between the predicted time point and the actual satellite shooting time point.

[0037] In a third step, in response to determining that the task consistency time difference is greater than a preset time difference threshold, an identifier representing a camera startup failure is determined as satellite camera startup failure information.

[0038] Step 1022: Perform satellite attitude anomaly detection on the satellite attitude data at the imaging moment to generate satellite attitude anomaly information.

[0039] In some embodiments, the execution subject may perform satellite attitude anomaly detection on the satellite attitude data at the imaging moment in various ways to generate satellite attitude anomaly information, wherein the satellite attitude anomaly information may indicate whether there is a fault in the satellite attitude.

[0040] In some optional implementations of some embodiments, the execution subject performs satellite attitude anomaly detection on the satellite attitude data at the imaging moment to generate satellite attitude anomaly information, which may include the following steps:

[0041] The first step is to obtain the satellite planning pose matrix of the satellite imaging mission, wherein the satellite planning pose matrix represents the satellite pose pre-planned according to the satellite imaging mission.

[0042] The second step is to determine the satellite attitude difference angle group between the satellite attitude data at the imaging moment and the satellite planning attitude matrix. The satellite attitude difference angle group may include satellite attitude difference angles representing the roll angle, pitch angle, and yaw angle, respectively. Here, the roll angle and pitch angle may be measured by two attitude measuring instruments. The yaw angle may be measured by a gyroscope.

[0043] The third step is to determine the difference between the satellite attitude data at the imaging moment and each satellite attitude difference angle in the satellite attitude difference angle group to generate a satellite roll angle error, a satellite pitch angle error, and a satellite yaw angle error. The difference between the pitch angle at the imaging moment, the roll angle at the imaging moment, and the yaw angle at the imaging moment in the satellite attitude data at the imaging moment and the corresponding satellite attitude difference angle can be determined as the satellite roll angle error, the satellite pitch angle error, and the satellite yaw angle error, respectively.

[0044] The fourth step is to generate an attitude error identifier characterizing the roll angle error, the pitch angle error and / or the yaw angle error in response to determining that the above-mentioned satellite roll angle error, the satellite pitch angle error and / or the satellite yaw angle error do not meet the corresponding preset error angle threshold.

[0045] In a fifth step, at least one attitude error identifier is determined as satellite attitude abnormality information, wherein the at least one attitude error identifier may indicate that there is at least one angle with a large error.

[0046] Step 1023, based on the satellite imaging time and image position coordinates, perform orbit prediction verification on the satellite to generate a satellite orbit prediction error.

[0047] In some embodiments, the execution subject may perform orbit prediction verification on the satellite based on the satellite imaging time and image position coordinates in various ways to generate a satellite orbit prediction error. The satellite orbit prediction error may indicate whether the predicted satellite orbit coordinates are abnormal.

[0048] In some optional implementations of some embodiments, the execution subject performs orbit prediction verification on the satellite based on the satellite imaging time and image position coordinates to generate a satellite orbit prediction error, which may include the following steps:

[0049] The first step is to obtain the satellite shooting coordinates of the satellite imaging mission, wherein the satellite shooting coordinates may be the on-orbit position of the satellite during the pre-generated imaging mission.

[0050] The second step is to determine the orbital coordinate error between the above-mentioned image position coordinates and the above-mentioned satellite shooting coordinates as the satellite orbit prediction error. Among them, first, the ground coordinates of the imaging task are converted from the earth's spherical coordinate system to the image coordinate system of the satellite image by means of coordinate conversion to obtain the converted imaging position coordinates. Then, the difference between the converted imaging position coordinates and the image center point coordinates of the satellite image is determined as the image coordinate difference. Afterwards, the above-mentioned image coordinate difference is normalized as an error weight. Here, the error weight can be a value between 0-1. Then, the product of the distance between the above-mentioned satellite shooting seat and the satellite shooting coordinates and the error weight is determined as the satellite orbit prediction error.

[0051] Here, the satellite orbit prediction error can represent the error between the pre-estimated satellite imaging coordinates and the actual satellite orbit. In practice, the image coordinate difference can be used to represent the error of the shooting center in the imaging task. And by converting it into a weight, the satellite orbit prediction error can be correlated and checked by the size of the position error of the shooting target. In this way, multi-dimensional correlation verification can be performed to improve the accuracy of shooting satellite images.

[0052] Step 1024, in response to determining that the satellite orbit prediction error is greater than a preset orbit error threshold, performing a time point check on the satellite to generate time point check information.

[0053] In some embodiments, the execution entity may perform a time point check on the satellite in response to determining that the satellite orbit prediction error is greater than a preset orbit error threshold in various ways to generate time point check information.

[0054] In some optional implementations of some embodiments, the execution subject performs time point verification on the satellite to generate time point verification information, which may include the following steps:

[0055] The first step is to obtain the satellite platform timestamp and the satellite original timestamp at the same time. The satellite platform timestamp and the satellite original timestamp can be timestamps of the same moment obtained at the same time. In practice, if there is a time synchronization problem between the satellite platform timestamp and the satellite original timestamp, then there will be errors in the timestamps at the same moment.

[0056] In the second step, in response to determining that the time difference between the satellite platform timestamp and the satellite original timestamp is greater than a preset time difference threshold, an identifier characterizing a calibration time anomaly is generated and determined as time point verification information.

[0057] Step 103, generating a satellite imaging error result based on the satellite camera startup failure information, satellite attitude abnormality information, satellite orbit prediction error and time point verification information.

[0058] In some embodiments, the above-mentioned execution entity can generate satellite imaging error results based on the above-mentioned satellite camera startup failure information, the above-mentioned satellite attitude abnormality information, the above-mentioned satellite orbit prediction error and the above-mentioned time point verification information in various ways.

[0059] In some optional implementations of some embodiments, the execution subject generates a satellite imaging error result based on the satellite camera startup fault information, the satellite attitude abnormality information, the satellite orbit prediction error and the time point verification information, which may include the following steps:

[0060] The first step is to select a fault factor identifier that matches the satellite camera startup fault information, the satellite attitude abnormality information, the satellite orbit prediction error, and the time point verification information from a preset fault information table. Among them, the fault information table can be an information table that is pre-set according to various abnormalities and the degree of abnormality. In practice, the fault information table may include various identifiers and data and corresponding fault factor identifiers. Thus, a fault factor identifier that matches the camera startup fault identifier, the attitude error identifier that characterizes the roll angle error, the pitch angle error, and / or the yaw angle error, the satellite orbit prediction error, and the identifier that characterizes the calibration time abnormality can be selected from the fault information table.

[0061] In the second step, at least one fault factor identifier is determined as a satellite imaging error result. If there are multiple identifiers or data belonging to the fault situation, multiple fault factor identifiers can be selected from the fault information table.

[0062] Step 104: Based on the satellite imaging error result, the satellite is adjusted for faults, and the adjusted satellite is used to capture images again.

[0063] In some embodiments, the execution subject may perform fault adjustment on the satellite based on the satellite imaging error result, and use the adjusted satellite to take images again. The fault adjustment on the satellite may be to adjust each data corresponding to the fault factor identifier.

[0064] As an example, if the fault factor identification indicates an orbit prediction failure, the orbit prediction can be performed again. If the fault factor identification indicates a timing failure, the satellite timestamp and the ground timestamp can be adjusted. If the fault factor identification indicates a satellite attitude failure, the corresponding attitude angle of the satellite can be adjusted.

[0065] The above steps 102-104 and their related contents, as an inventive point of an embodiment of the present disclosure, solve the second technical problem mentioned in the background technology: "In the inspection process, only each type of data is analyzed, and the analysis dimension is relatively single. The satellite imaging error in orbit may come from multiple factors, such as orbit prediction error, satellite attitude control abnormality, camera abnormality, etc. It is difficult to integrate multiple dimensions of data information for judgment, which may lead to a single thinking of complex problems and difficulty in solving the problem comprehensively. As a result, it is difficult for the satellite to take images more accurately after adjustment." The factors that make it difficult for the satellite to take images more accurately after adjustment are often as follows: In the inspection process, only each type of data is analyzed, and the analysis dimension is relatively single. The satellite imaging error in orbit may come from multiple factors, such as orbit prediction error, satellite attitude control abnormality, camera abnormality, etc. It is difficult to integrate multiple dimensions of data information for judgment, which may lead to a single thinking of complex problems and difficulty in solving the problem comprehensively. In order to achieve this effect, firstly, through task consistency detection, satellite attitude abnormality detection, orbit prediction verification, and time point verification, satellite fault troubleshooting can be performed from multiple dimensions. At the same time, the image coordinate difference can be used to characterize the error of the shooting center in the imaging task. The conversion into weights can be used to correlate and check the satellite orbit prediction error by the size of the position error of the shooting target. Therefore, multi-dimensional correlation verification can be performed to improve the accuracy of shooting satellite images. In addition, by introducing a fault information table, it can be used to further improve the efficiency of locating fault problems. Therefore, not only can the time for locating faults be shortened, but also the problem of satellite shooting can be solved by timely satellite adjustment. Furthermore, the adjusted satellite can perform shooting tasks more accurately and improve the accuracy of captured images.

[0066] Optionally, the execution entity may also store the images and various data taken by the satellite for subsequent maintenance and updating of the fault information table.

[0067] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the satellite image shooting method of some embodiments of the present disclosure, the consumption of satellite shooting resources can be reduced. Specifically, the reason for wasting satellite shooting resources is that the transit time of satellite shooting is short, and remote adjustment requires repeated communication with the satellite through the ground station, and it is difficult to adjust to the appropriate degree in time. As a result, it is easy to miss the opportunity to shoot satellites. Based on this, the satellite image shooting method of some embodiments of the present disclosure first obtains satellite imaging position information. Among them, the satellite imaging position information includes: image position coordinates, imaging timestamp and satellite attitude data at the imaging moment. Then, in response to determining that the error of the image position coordinates in the above satellite imaging position information is greater than the preset position error threshold, the following satellite imaging troubleshooting steps are performed: the above imaging timestamp is subjected to task consistency detection to generate satellite camera startup fault information. The satellite attitude data at the above imaging moment is subjected to satellite attitude anomaly detection to generate satellite attitude anomaly information. Based on the above satellite imaging moment and image position coordinates, the above satellite is subjected to orbit prediction verification to generate a satellite orbit prediction error. In response to determining that the satellite orbit prediction error is greater than the preset orbit error threshold, the satellite is checked at a time point to generate time point verification information. Considering that the ground station adjustment requires communication and it is difficult to control the adjustment strength, in order to avoid missing the satellite transit time, by setting task consistency detection, satellite attitude anomaly detection, orbit prediction verification and time point verification, satellite fault troubleshooting can be automatically performed. Thus, the time to determine the fault problem is shortened. At the same time, troubleshooting in a multi-dimensional parallel manner can not only shorten the time to determine the fault, but also locate the fault problem from multiple dimensions, so as to facilitate targeted satellite adjustment. Then, based on the satellite camera startup fault information, the satellite attitude anomaly information, the satellite orbit prediction error and the time point verification information, a satellite imaging error result is generated. Thus, it can be used to locate the fault problem of satellite shooting. Finally, based on the satellite imaging error result, the satellite is adjusted for the fault, and the adjusted satellite is used to shoot the image again. Thus, the efficiency of fault adjustment can be greatly improved to avoid missing the satellite transit time. Then, the consumption of satellite shooting resources is reduced.

[0068] Further references Figure 2 As an implementation of the methods shown in the above figures, the present disclosure provides some embodiments of a satellite image shooting device. These device embodiments are similar to Figure 1 Corresponding to the method embodiments shown, the device can be specifically applied to various electronic devices.

[0069] like Figure 2As shown, the satellite image shooting device 200 of some embodiments includes: an acquisition unit 201, a troubleshooting unit 202, a generation unit 203, and an adjustment and shooting unit 204. The acquisition unit 201 is configured to acquire satellite imaging position information, wherein the satellite imaging position information includes: image position coordinates, imaging timestamp, and satellite attitude data at the imaging moment; the troubleshooting unit 202 is configured to, in response to determining that the error of the image position coordinates in the above satellite imaging position information is greater than a preset position error threshold, perform the following satellite imaging troubleshooting steps: perform task consistency detection on the above imaging timestamp to generate satellite camera startup fault information; perform satellite attitude anomaly detection on the above satellite attitude data at the imaging moment to generate satellite attitude anomaly information; based on the above satellite imaging time and image, perform task consistency detection on the above satellite attitude data at the imaging moment to generate satellite attitude anomaly information; based on the above satellite imaging time and image, perform task consistency detection on the above satellite attitude data at the imaging moment to generate satellite attitude anomaly information; based on the above satellite imaging time and image, perform task consistency detection on the above satellite attitude data at the imaging moment to generate satellite attitude anomaly information; based on the above satellite imaging time and image, perform task consistency detection on the above satellite image position coordinates. The image position coordinates are used to perform orbit prediction verification on the above-mentioned satellite to generate a satellite orbit prediction error; in response to determining that the above-mentioned satellite orbit prediction error is greater than a preset orbit error threshold, a time point verification is performed on the above-mentioned satellite to generate time point verification information; the generation unit 203 is configured to generate a satellite imaging error result based on the above-mentioned satellite camera startup fault information, the above-mentioned satellite attitude abnormality information, the above-mentioned satellite orbit prediction error and the above-mentioned time point verification information; the adjustment and shooting unit 204 is configured to perform fault adjustment on the above-mentioned satellite based on the above-mentioned satellite imaging error result, and use the adjusted satellite to shoot images again.

[0070] It is understood that the units described in the device 200 are similar to those described in the reference Figure 1 Therefore, the operations, features and beneficial effects described above for the method are also applicable to the device 200 and the units included therein, and will not be described in detail here.

[0071] Reference below Figure 3 , which shows a structural schematic diagram of an electronic device (eg, a computing device) 300 suitable for implementing some embodiments of the present disclosure. Figure 3 The electronic device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present disclosure.

[0072] like Figure 3 As shown, the electronic device 300 may include a processing device (e.g., a central processing unit, a graphics processing unit, etc.) 301, which can perform various appropriate actions and processes according to a program stored in a read-only memory 302 or a program loaded from a storage device 308 into a random access memory 303. Various programs and data required for the operation of the electronic device 300 are also stored in the random access memory 303. The processing device 301, the read-only memory 302, and the random access memory 303 are connected to each other via a bus 304. An input / output interface 305 is also connected to the bus 304.

[0073] Typically, the following devices may be connected to the I / O interface 305: an input device 306 including, for example, a touch screen, a touch pad, a keyboard, a mouse, a camera, a microphone, an accelerometer, a gyroscope, etc.; an output device 307 including, for example, a liquid crystal display (LCD), a speaker, a vibrator, etc.; a storage device 308 including, for example, a magnetic tape, a hard disk, etc.; and a communication device 309. The communication device 309 may allow the electronic device 300 to communicate with other devices wirelessly or by wire to exchange data. Figure 3 The electronic device 300 is shown with various devices, but it should be understood that it is not required to implement or possess all the devices shown. More or fewer devices may be implemented or possessed instead. Figure 3 Each block shown in the figure may represent one device, or may represent multiple devices as required.

[0074] In particular, according to some embodiments of the present disclosure, the process described above with reference to the flowchart can be implemented as a computer software program. For example, some embodiments of the present disclosure include a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program contains program code for executing the method shown in the flowchart. In some such embodiments, the computer program can be downloaded and installed from the network through the communication device 309, or installed from the storage device 308, or installed from the read-only memory 302. When the computer program is executed by the processing device 301, the above-mentioned functions defined in the method of some embodiments of the present disclosure are executed.

[0075] It should be noted that the computer-readable medium recorded in some embodiments of the present disclosure may be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In some embodiments of the present disclosure, a computer-readable storage medium may be any tangible medium containing or storing a program, which may be used by or in combination with an instruction execution system, device or device. In some embodiments of the present disclosure, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. Computer readable signal media may also be any computer readable medium other than computer readable storage media, which may send, propagate or transmit a program for use by or in conjunction with an instruction execution system, apparatus or device. The program code contained on the computer readable medium may be transmitted using any appropriate medium, including but not limited to: wires, optical cables, RF (radio frequency), etc., or any suitable combination of the above.

[0076] In some embodiments, the client and the server may communicate using any currently known or future developed network protocol such as HTTP (Hyper Text Transfer Protocol), and may be interconnected with any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include a local area network ("LAN"), a wide area network ("WAN"), an internet (e.g., the Internet), and a peer-to-peer network (e.g., an ad hoc peer-to-peer network), as well as any currently known or future developed network.

[0077] The computer-readable medium may be included in the electronic device, or may exist independently without being incorporated into the electronic device. The computer-readable medium carries one or more programs. When the one or more programs are executed by the electronic device, the electronic device: obtains satellite imaging position information, wherein the satellite imaging position information includes: image position coordinates, imaging timestamp and satellite attitude data at the imaging time; in response to determining that the error of the image position coordinates in the satellite imaging position information is greater than a preset position error threshold, performs the following satellite imaging troubleshooting steps: performs task consistency detection on the imaging timestamp to generate satellite camera startup fault information; performs satellite attitude anomaly detection on the satellite attitude data at the imaging time to generate satellite attitude anomaly information; based on the satellite imaging time and image position coordinates, performs orbit prediction verification on the satellite to generate a satellite orbit prediction error; in response to determining that the satellite orbit prediction error is greater than the preset orbit error threshold, performs time point verification on the satellite to generate time point verification information; generates a satellite imaging error result based on the satellite camera startup fault information, the satellite attitude anomaly information, the satellite orbit prediction error and the time point verification information; based on the satellite imaging error result, performs fault adjustment on the satellite, and uses the adjusted satellite to take images again.

[0078] Computer program code for performing the operations of some embodiments of the present disclosure may be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0079] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present disclosure. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0080] The units described in some embodiments of the present disclosure may be implemented by software or hardware. The units described may also be set in a processor, for example, it may be described as: a processor includes an acquisition unit, a troubleshooting unit, a generation unit, an adjustment unit, and a shooting unit. The names of these units do not constitute limitations on the units themselves in some cases, for example, the acquisition unit may also be described as a "unit for acquiring satellite imaging position information".

[0081] The functions described above herein may be performed at least in part by one or more hardware logic components. For example, without limitation, exemplary types of hardware logic components that may be used include: field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chips (SOCs), complex programmable logic devices (CPLDs), and the like.

[0082] The above descriptions are only some preferred embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the embodiments of the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above inventive concept. For example, the above features are replaced with (but not limited to) technical features with similar functions disclosed in the embodiments of the present disclosure.

Claims

1. A satellite image shooting method, comprising: Obtain satellite imaging position information, wherein the satellite imaging position information includes: image position coordinates, imaging timestamp and satellite attitude data at the imaging time; In response to determining that the error of the image position coordinates in the satellite imaging position information is greater than a preset position error threshold, performing the following satellite imaging troubleshooting steps: Performing a task consistency check on the imaging timestamp to generate satellite camera startup failure information; Performing satellite attitude anomaly detection on the satellite attitude data at the imaging moment to generate satellite attitude anomaly information; Based on the satellite imaging time and the image position coordinates, performing orbit prediction verification on the satellite to generate a satellite orbit prediction error; In response to determining that the satellite orbit prediction error is greater than a preset orbit error threshold, performing a time point check on the satellite to generate time point check information; Generate a satellite imaging error result based on the satellite camera startup failure information, the satellite attitude abnormality information, the satellite orbit prediction error and the time point verification information; Based on the satellite imaging error result, performing fault adjustment on the satellite, and taking images again using the adjusted satellite; Get the ground coordinates of the imaging mission; Determine the latitude and longitude errors between the image position coordinates and the imaging task ground coordinates as image position coordinate errors; The step of performing orbit prediction verification on the satellite based on the satellite imaging time and image position coordinates to generate a satellite orbit prediction error includes: Get satellite acquisition coordinates for satellite imaging missions; Determine the orbital coordinate error between the image position coordinate and the satellite shooting coordinate as the satellite orbit prediction error; The performing time point verification on the satellite to generate time point verification information includes: Acquire the satellite platform timestamp and the satellite original timestamp at the same time; In response to determining that the time difference between the satellite platform timestamp and the satellite original timestamp is greater than a preset time difference threshold, an identifier characterizing a calibration time anomaly is generated and determined as time point verification information.

2. The method according to claim 1, wherein: The generating of a satellite imaging error result based on the satellite camera startup fault information, the satellite attitude abnormality information, the satellite orbit prediction error and the time point verification information includes: Selecting a fault factor identifier that matches the satellite camera startup fault information, the satellite attitude abnormality information, the satellite orbit prediction error and the time point verification information from a preset fault information table; At least one fault factor identification is determined as a result of a satellite imaging error.

3. A satellite image shooting device, comprising: An acquisition unit is configured to acquire satellite imaging position information, wherein the satellite imaging position information includes: image position coordinates, imaging timestamp and satellite attitude data at the imaging moment; The troubleshooting unit is configured to, in response to determining that the error of the image position coordinates in the satellite imaging position information is greater than a preset position error threshold, perform the following satellite imaging troubleshooting steps: Performing a task consistency check on the imaging timestamp to generate satellite camera startup failure information; Performing satellite attitude anomaly detection on the satellite attitude data at the imaging moment to generate satellite attitude anomaly information; Based on the satellite imaging time and the image position coordinates, performing orbit prediction verification on the satellite to generate a satellite orbit prediction error; In response to determining that the satellite orbit prediction error is greater than a preset orbit error threshold, performing a time point check on the satellite to generate time point check information; A generating unit configured to generate a satellite imaging error result based on the satellite camera startup failure information, the satellite attitude abnormality information, the satellite orbit prediction error and the time point verification information; An adjustment and shooting unit, configured to perform fault adjustment on the satellite based on the satellite imaging error result, and to use the adjusted satellite to shoot images again; Get the ground coordinates of the imaging mission; Determine the latitude and longitude errors between the image position coordinates and the imaging task ground coordinates as image position coordinate errors; The step of performing orbit prediction verification on the satellite based on the satellite imaging time and image position coordinates to generate a satellite orbit prediction error includes: Get satellite acquisition coordinates for satellite imaging missions; Determine the orbital coordinate error between the image position coordinate and the satellite shooting coordinate as the satellite orbit prediction error; The performing time point verification on the satellite to generate time point verification information includes: Acquire the satellite platform timestamp and the satellite original timestamp at the same time; In response to determining that the time difference between the satellite platform timestamp and the satellite original timestamp is greater than a preset time difference threshold, an identifier characterizing a calibration time anomaly is generated and determined as time point verification information.

4. An electronic device, comprising: one or more processors; a storage device having one or more programs stored thereon, When the one or more programs are executed by the one or more processors, the one or more processors implement the method according to any one of claims 1-2.

5. A computer readable medium having a computer program stored thereon, wherein: When the computer program is executed by a processor, the method according to any one of claims 1 to 2 is implemented.

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