Satellite multi-load monthly forecasting method and device and electronic equipment

Abstract

The invention provides a satellite multi-load moon forecasting method and device and electronic equipment. The method comprises the following steps: acquiring coordinates of a satellite moon vector connecting line under preset time precision in an instrument coordinate system; performing cold air view field constraint, scanning view field constraint, earth night side observation constraint and lunar phase angle constraint on each instrument to obtain a rough time window of the moon entering the view field corresponding to each instrument; and carrying out dynamic adaptive golden section extremum search at a preset time interval, calculating the visibility of each instrument view field to the moon, and obtaining the optimal observation time of the moon. According to the satellite multi-load lunar forecasting method and device and the electronic equipment provided by the embodiment of the invention, the FY-3 F satellite multi-load lunar observation rapid forecasting method based on the combination of rough time search and adaptive golden section extremum search is constructed, and by optimizing the calculation of the cold air view field and the scanning view field angle, the accuracy of lunar observation is improved. The moon forecasting method for the cross-rail circular scanning instrument is provided, and limitation of a traditional rectangular view field is avoided.

Description

Technical Field

[0001] The present application belongs to the field of lunar observation technology, and in particular relates to a satellite multi-payload lunar prediction method, device and electronic equipment. Background Art

[0002] The Moon, with its stable spectral radiation and moderate irradiance, is an ideal reference source for on-orbit radiometric calibration of space-based optical remote sensors. Because the Moon is globally visible, Earth-orbiting satellites can observe it through specific geometries. Satellite lunar calibration can be performed in two modes: passive and active. In passive calibration mode, the Moon randomly enters the detector's field of view, suitable for both geostationary and polar-orbiting satellites. Active calibration mode requires the satellite to adjust its attitude to point toward the Moon for imaging. To prevent attitude maneuvers from interfering with other payloads, the Fengyun-3F (FY-3F) satellite uses passive calibration mode. Because the Moon's presence in the payload's field of view is short, accurately calculating the duration of lunar imaging is crucial.

[0003] Existing methods include the high-precision model based on STK (a system analysis software developed by Analytical Graphics Inc. in the United States) proposed by Zhu Jun et al., which has high accuracy but consumes a lot of computing resources; the prediction algorithm using orbital elements by Chen Lin et al. is accurate but inefficient; the Fibonacci search method proposed by Jiang Chengzhou et al. improves the calculation speed, but its imaging constraints are only applicable to area array cameras and are not applicable to Fengyun satellite payloads with circular scanning; Wu Ronghua et al. use GPS and attitude data to extract lunar images, but are not suitable for time window prediction.

[0004] The Fengyun-3F satellite (FY-3F) carries multiple cross-orbit circular scanning payloads. Its scanning components can be used for lunar calibration through the cold sky field of view every time it rotates. How to construct a lunar prediction constraint model based on its unique imaging method and improve the efficiency of lunar prediction with the coordination of multiple payloads remains an urgent problem to be solved. Summary of the Invention

[0005] To solve the existing technical problems, the embodiments of the present invention provide a satellite multi-payload monthly forecasting method, device and electronic equipment.

[0006] In the first aspect, an embodiment of the present application provides a satellite multi-payload lunar forecasting method, including: obtaining the coordinates of the satellite-moon vector line in the instrument coordinate system with a preset time accuracy; based on the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument, performing cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints and lunar phase angle constraints on each instrument respectively, to obtain a rough time window for the moon to enter the field of view corresponding to each instrument; based on the rough time window for the moon to enter the field of view corresponding to each instrument, performing a dynamic adaptive golden section extreme value search at a preset time interval, calculating the visibility of the moon in the field of view of each instrument, and obtaining the optimal observation time of the moon.

[0007] Optionally, the coordinates of the satellite-moon vector line in the instrument coordinate system at a preset time accuracy are obtained, including: based on a simplified perturbation orbit model, combined with the JPL ephemeris and the satellite's two-row orbit elements, obtaining the position information of the satellite, moon, earth and sun in the J2000 geocentric inertial coordinate system; converting the J2000 geocentric inertial coordinate system into a satellite orbit coordinate system, and then converting the satellite orbit coordinate system into a satellite body coordinate system; and calculating the satellite-moon vector line of each device in the instrument coordinate system according to the installation matrix of each device.

[0008] Optionally, the calculation formula for the satellite-moon vector connection line of each device in the instrument coordinate system is: where R body-ins is the transformation matrix from the satellite body coordinate system to the instrument coordinate system, R orb-body is the transformation matrix from the satellite orbit coordinate system to the satellite body coordinate system, R J2000-orb is the transformation matrix from the J2000 geocentric inertial coordinate system to the satellite orbit coordinate system, r moon and r satellite are the positions of the moon and satellite in the J2000 geocentric inertial coordinate system, s represents the distance between the moon and satellite, and u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

[0009] Optionally, before the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument are used to constrain each instrument respectively, cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints and lunar phase angle constraints are obtained, and the rough time window for the moon to enter the field of view corresponding to each instrument is obtained, the method also includes: calculating the cold sky field of view angle and scanning field of view angle of each device according to the circular scanning direction.

[0010] Optionally, the calculation formula for the scanning field angle is: α = 90-arccos(u x / norm(u moon )), where α represents the angle between the satellite moon vector and the YOZ plane of the instrument coordinate system, u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

[0011] Optionally, the calculation formula for the cold sky field of view angle is: Where β represents the angle between the satellite moon vector and the +Y axis of the instrument coordinate system, u y and u z They are respectively the components of the satellite-moon vector line in the Y and Z directions in the instrument coordinate system.

[0012] In the second aspect, an embodiment of the present application provides a satellite multi-payload lunar forecasting device, including: a coordinate acquisition module, a rough calculation module and an optimal solution calculation module; the coordinate acquisition module is used to obtain the coordinates of the satellite-moon vector connection line in the instrument coordinate system under a preset time accuracy; the rough calculation module is used to perform cold sky field of view constraints, scanning field of view constraints, earth night side observation constraints and lunar phase angle constraints on each instrument based on the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument, and obtain the rough time window of the moon entering the field of view corresponding to each instrument; the optimal solution calculation module is used to perform dynamic adaptive golden section extreme value search at preset time intervals based on the rough time window of the moon entering the field of view corresponding to each instrument, calculate the visibility of the moon in the field of view of each instrument, and obtain the optimal observation time of the moon.

[0013] In a third aspect, an embodiment of the present invention provides a computer device comprising a processor and a memory, wherein the memory stores a computer program, and the processor executes the computer program stored in the memory. When the computer program is executed by the processor, the satellite multi-payload monthly forecast method described in the first aspect is implemented.

[0014] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the satellite multi-payload monthly forecasting method described in the first aspect above.

[0015] In a fifth aspect, an embodiment of the present application provides a computer program product. When the computer program product is run on a computer device, the computer device executes the satellite multi-payload monthly forecasting method described in any one of the first aspects above.

[0016] It can be understood that the beneficial effects of the second to fifth aspects mentioned above can be found in the relevant description of the first aspect mentioned above, and will not be repeated here.

[0017] Compared with the prior art, the beneficial effects of the embodiments of the present application are as follows: through the satellite multi-payload lunar forecasting method provided by the embodiments of the present invention, first, the search range is narrowed by a rough time search, and the coordinates of the satellite-moon vector connection line in the instrument coordinate system with rough time accuracy are obtained. Based on this, the cold sky field of view angle and the scanning field of view angle are calculated according to the circular scanning direction, and the cold sky field of view range, the scanning field of view range and the moon phase illumination of each instrument are combined to perform constraints, so as to obtain a rough time window for the moon to enter the field of view of each instrument. Further, based on the fast search strategy of the dynamic adaptive golden section extreme value search method, the segmentation ratio is dynamically adjusted, the visibility of each instrument's field of view to the moon is calculated, and the optimal observation time of the moon for each instrument is obtained. This method can realize the rapid and autonomous prediction of the best observation points of the moon for the FY-3F satellite multi-payload.

[0018] It can be understood that the present invention constructs a rapid prediction method for lunar observations of the Fengyun-3F satellite multi-payload based on the combination of rough time search and adaptive golden section extreme value search. By optimizing the calculation of the cold sky field of view and the scanning field of view angle, a lunar prediction method for cross-orbit circular scanning instruments is proposed, avoiding the limitations of the traditional rectangular field of view. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments or descriptions of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] Figure 1 A flowchart of a satellite multi-payload monthly forecasting method provided by an embodiment of the present invention is shown;

[0021] Figure 2 A flowchart of calculating a rough time window for a multi-payload monthly forecast in a satellite multi-payload monthly forecast method provided by an embodiment of the present invention is shown;

[0022] Figure 3 A flowchart of subsequent processing for a rough time window of a multi-load monthly report according to an embodiment of the present invention is shown;

[0023] Figure 4 A flowchart of obtaining the coordinates of the satellite-moon vector line in the instrument coordinate system at a preset time accuracy according to an embodiment of the present invention is shown;

[0024] Figure 5 A schematic structural diagram of a satellite multi-payload monthly forecasting device provided in an embodiment of the present invention is shown;

[0025] Figure 6A schematic structural diagram of an electronic device for executing a satellite multi-payload monthly forecasting method provided by an embodiment of the present invention is shown. DETAILED DESCRIPTION

[0026] In the following description, specific details such as specific system structures and techniques are provided for purposes of illustration rather than limitation to facilitate a thorough understanding of the embodiments of the present application. However, it will be apparent to those skilled in the art that the present application may be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid obscuring the description of the present application with unnecessary detail.

[0027] It should be understood that when used in the present specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or collections thereof.

[0028] It will also be understood that the term "and / or" used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.

[0029] As used in this specification and the appended claims, the term "if" can be interpreted as "when" or "upon" or "in response to determining" or "in response to detecting," depending on the context. Similarly, the phrase "if it is determined" or "if [described condition or event] is detected" can be interpreted as meaning "upon determination" or "in response to determining" or "upon detection of [described condition or event]" or "in response to detecting [described condition or event]," depending on the context.

[0030] In addition, in the description of the present application specification and the appended claims, the terms "first", "second", "third", etc. are only used to distinguish the descriptions and cannot be understood as indicating or implying relative importance.

[0031] References to "one embodiment" or "some embodiments" in this specification mean that a particular feature, structure, or characteristic described in conjunction with that embodiment is included in one or more embodiments of the present application. Thus, phrases such as "in one embodiment," "in some embodiments," "in other embodiments," and "in other embodiments" appearing in various places in this specification do not necessarily refer to the same embodiment, but rather mean "one or more but not all embodiments," unless otherwise specifically emphasized. The terms "including," "comprising," "having," and variations thereof all mean "including but not limited to," unless otherwise specifically emphasized.

[0032] The present invention proposes a rapid prediction method for lunar observations by the FY-3F (Fengyun-3F) satellite's cross-orbit circular scanning payload. The FY-3F satellite carries 10 advanced remote sensing instruments, including the MERSI-III (Medium Resolution Spectroradiometer-III), MWTS-III (Microwave Thermometer-III), MWHS-II (Microwave Hygrometer-II), ERM-II (Earth Radiation Sounder-II), and HIRAS-II (Hyperspectral Infrared Atmospheric Sounder-II). Five of these instruments have lunar calibration capabilities. Common operating modes for these instruments (also referred to as payloads) include Earth observation mode, internal calibration mode, and lunar calibration mode. Each rotation of the instrument's scanning component sequentially scans Earth targets, an onboard calibrator, the Sun, and a cold sky field of view, acquiring data for each of the four observation targets. The cold sky field of view can be used for lunar calibration. During lunar calibration, a cold sky reference is established in cold space, followed by a gaze at the Moon. Finally, a new cycle begins with a scan back to cold space. It is understandable that, unlike other mobile lunar observation payloads, the FY-3F satellite needs to increase the cold sky field of view to constrain its working mode.

[0033] However, the inventors discovered that existing methods only calculate constraints on the scanning field of view angle and assume a rectangular imaging area. This method is limited in that it fails to fully consider cold-air field of view constraints and cannot adapt to payload scanning points of varying shapes. In other words, its imaging constraints only apply to area array cameras and are not applicable to Fengyun satellite payloads that scan circularly.

[0034] The technical solutions in the embodiments of the present application are described in detail below.

[0035] Figure 1 FIG1 shows a flow chart of a satellite multi-payload monthly forecasting method provided by an embodiment of the present invention. Figure 1 As shown, the method includes the following steps 101-103.

[0036] Step 101: Obtain the coordinates of the satellite-moon vector line in the instrument coordinate system at a preset time accuracy.

[0037] Lunar calibration for polar-orbiting satellites requires determining the relative positions, velocities, and geometric relationships of the Sun, Moon, Earth, and satellite. These parameters vary at different times. Only when the positions and geometric relationships of all celestial bodies meet the geometric constraints for lunar calibration and the Moon is within the field of view of the satellite's instruments can the specific times of the Moon's entry and exit from view be calculated. During normal orbital flight, the vector pointing toward the Moon rotates once about the +Y axis of the satellite's orbital system. The Moon appears in the instrument's field of view only when the Moon's vector lies within the YOZ plane. This rotation of the Moon's vector limits this timeframe.

[0038] In an embodiment of the present invention, a rough preset time accuracy, such as one minute, and a forecast time, such as one month in the future, can be first set to obtain the coordinates of the satellite-moon vector line in the instrument coordinate system with a time interval of one minute at a certain time in the future (such as one month in the future).

[0039] Step 102: Based on the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument, each instrument is subjected to cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints and lunar phase angle constraints to obtain the rough time window of the moon entering the field of view corresponding to each instrument.

[0040] When calculating lunar visibility, the first geometric constraints that must be met are the lunar phase angle constraint and the Earth night-side observation constraint. Specifically, the lunar phase angle is calculated to ensure that the lunar phase angle geometric constraint is satisfied, and the geometric relationship between the Sun, satellite, and Earth is calculated to ensure that the Earth night-side observation constraint is satisfied.

[0041] Specifically, the moon orbits the Earth over a monthly cycle, causing the relative positions of the moon, sun, and satellite to vary regularly. The lunar phase angle is defined as the angle between the line connecting the satellite payload and the moon, and the line connecting the moon and sun. Satellite calibration is typically performed when the lunar surface brightness exceeds 50%, meaning the lunar phase angle ranges from -90° to +90°.

[0042] Secondly, to avoid direct sunlight and ensure effective observation, the satellite must be located on the night side of the Earth. By calculating the geometric relationship between the sun, satellite, and Earth, it is determined whether the satellite is on the night side of the Earth, thereby satisfying the constraints of Earth night side observation. The calculation formula is: in represents the vector from the Earth's mass center to the Sun's mass center, represents the vector from the Earth's center of mass to the satellite's center of mass, represents the vector from the moon's mass center to the sun's mass center, Represents the vector pointing from the moon's center of mass to the sensor's center of mass.

[0043] Furthermore, in order to ensure that satellite instruments can meet the requirements of cold sky field of view and scanning field of view, two key angles need to be calculated: scanning field of view angle α and cold sky field of view angle β. Through the cold sky field of view angle, scanning field of view angle and moon phase illumination of each instrument mentioned above, each instrument is subjected to cold sky field of view constraints, scanning field of view constraints, earth night side observation constraints and moon phase angle constraints respectively, and the rough time window of the moon entering the field of view corresponding to each instrument can be obtained. In other words, this embodiment comprehensively considers the constraints such as the cold sky field of view range, scanning field of view range and moon phase illumination of each instrument, thereby calculating the rough time window in which each instrument can observe the moon under the constraints. You can refer to Figure 2 As shown, Figure 2 A flow chart of calculating a rough time window for a multi-load monthly report according to an embodiment of the present invention is shown.

[0044] Step 103: Based on the rough time window of the moon entering the field of view corresponding to each instrument, a dynamic adaptive golden section extreme value search is performed at a preset time interval to calculate the visibility of the moon in the field of view of each instrument and obtain the optimal observation time of the moon.

[0045] After obtaining the approximate time window for the moon's entry into view for each instrument based on step 102, this embodiment of the present invention proposes a rapid search strategy based on a dynamic adaptive golden section extreme value search method. This strategy designs a convergence criterion that combines an interval length threshold with the KL divergence probability distribution criterion. By dynamically adjusting the segmentation ratio based on historical iterative gradients, the optimal solution (i.e., the optimal lunar observation time for each instrument) is found, enabling rapid and autonomous prediction of the optimal lunar observation points for the FY-3F satellite's multiple payloads. For example, based on each rough observation time, a dynamic adaptive golden section extreme value search is performed within 1-minute intervals to calculate the lunar visibility of the instrument's field of view and determine the optimal lunar observation time.

[0046] Specifically, the traditional golden section search continuously approaches the optimal solution by fixing the segmentation ratio and obtains the optimal observation time. The formula is as follows: Here, a and c are the left and right boundaries of the current search interval, and b is the split point. This ratio ensures that the search interval is optimally split at each iteration. In this way, the golden section search can quickly find the optimal solution among multiple candidate solutions. To further improve search accuracy, the embodiment of the present invention introduces a dynamic adjustment mechanism into this strategy. Specifically, during the search process, the split ratio λ is adaptively adjusted based on gradient information. The adjustment formula is: Among them, λ t is the current segmentation ratio, λ t+1 is the next segmentation ratio, γ is the adjustment factor, is the current position x tThrough this dynamic adjustment mechanism, the segmentation ratio can be flexibly adjusted according to the function change trend, thereby improving the efficiency and accuracy of the search.

[0047] In addition, in order to ensure that the search process reaches the predetermined accuracy within a limited time, the embodiment of the present invention also introduces a convergence criterion based on interval length and KL divergence. First, in each iteration, the current search interval length L is calculated. t =ca. When it is less than the preset threshold value L min When , the search is considered to have converged and the iteration is stopped. Finally, in order to ensure the stability and accuracy of the search results, the embodiment of the present invention also introduces KL divergence as an evaluation criterion. The KL divergence D KL (P||Q) is defined as: Among them, P(x i ) and Q(x i ) are the probability distributions of the current iteration and the target distribution respectively. Figure 3 As shown, Figure 3 A flow chart of subsequent processing for a rough time window of a multi-load monthly report according to an embodiment of the present invention is shown.

[0048] The satellite multi-payload lunar prediction method provided by the embodiment of the present invention first narrows the search range through a rough time search to obtain the coordinates of the satellite-moon vector connection line in the instrument coordinate system with rough time accuracy. Based on this, the cold sky field of view angle and the scanning field of view angle are calculated according to the circular scanning direction, and the cold sky field of view range, scanning field of view range and moon phase illumination of each instrument are combined to perform constraints, thereby obtaining a rough time window for the moon to enter the field of view of each instrument. Further, based on the fast search strategy of the dynamic adaptive golden section extreme value search method, the segmentation ratio is dynamically adjusted, the visibility of each instrument's field of view to the moon is calculated, and the optimal observation time of the moon for each instrument is obtained. This method can realize the rapid and autonomous prediction of the best observation points of the moon for the FY-3F satellite multi-payload.

[0049] It can be understood that the present invention constructs a rapid prediction method for lunar observations of the Fengyun-3F satellite multi-payload based on the combination of rough time search and adaptive golden section extreme value search. By optimizing the calculation of the cold sky field of view and the scanning field of view angle, a lunar prediction method for cross-orbit circular scanning instruments is proposed, avoiding the limitations of the traditional rectangular field of view.

[0050] Alternatively, as Figure 4 As shown, the above step 101 "obtaining the coordinates of the satellite-moon vector connection line in the instrument coordinate system under the preset time accuracy" includes the following steps 1011-1013.

[0051] Step 1011: Based on the simplified perturbation orbit model, combined with the JPL ephemeris and the two-line orbit elements of the satellite, the position information of the satellite, the moon, the earth and the sun in the J2000 geocentric inertial coordinate system is obtained.

[0052] The embodiment of the present invention is based on a simplified perturbation orbit model, namely the SGP4 model (the Simplified General Perturbations 4 model is a simplified perturbation orbit model used to calculate satellite orbital position and velocity), combined with the JPL ephemeris and two rows of satellite orbital elements to obtain the position information of the satellite, moon, earth and sun in the J2000 geocentric inertial coordinate system.

[0053] Step 1012: Convert the J2000 geocentric inertial coordinate system into the satellite orbit coordinate system, and then convert the satellite orbit coordinate system into the satellite body coordinate system.

[0054] Step 1013: Calculate the satellite-moon vector connection line of each device in the instrument coordinate system based on the installation matrix of each device.

[0055] Optionally, the calculation formula for the satellite-moon vector connection line of each device in the instrument coordinate system is: where R body-ins is the transformation matrix from the satellite body coordinate system to the instrument coordinate system, R orb-body is the transformation matrix from the satellite orbit coordinate system to the satellite body coordinate system, R J2000-orb is the transformation matrix from the J2000 geocentric inertial coordinate system to the satellite orbit coordinate system, r moon and r satellite are the positions of the moon and satellite in the J2000 geocentric inertial coordinate system, s is the distance between the moon and satellite, and u is the distance between the moon and satellite. moon Indicates the satellite-moon vector line in the instrument coordinate system (it should be noted that u moon It can also be understood as the unit vector of the star-moon vector in the instrument coordinate system), u x ,u y ,u z u moon Components in the XYZ directions.

[0056] Optionally, before the above step 102 "based on the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument, each instrument is subjected to cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints and lunar phase angle constraints to obtain a rough time window for the moon to enter the field of view corresponding to each instrument", the method also includes: calculating the cold sky field of view angle and scanning field of view angle of each device according to the circular scanning direction.

[0057] Unlike the prior art, an embodiment of the present invention proposes a new method for cross-track circular scanning instruments. In an embodiment of the present invention, the scanning field of view angle can be set to angle α, which is the angle between the star-moon vector and the YOZ plane of the instrument coordinate system, to ensure that the star-moon vector is within the scanning field of view; the cold sky field of view angle is set to angle β, which is the angle between the star-moon vector and the +Y axis of the instrument coordinate system, to ensure that the star-moon vector is within the cold sky field of view. The design of these two angles not only takes into account the cold sky field of view constraints, but also specifically optimizes for the case where the payload scanning point is circular, avoiding the limitation of only considering the rectangular field of view in the traditional method.

[0058] Specifically, the calculation formula of the scanning field angle α is: α=90-arccos(u x / norm(u moon )), where α represents the angle between the satellite moon vector and the instrument coordinate system YOZ plane, u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

[0059] Specifically, the calculation formula for the cold sky viewing angle β is: Where β represents the angle between the satellite moon vector and the +Y axis of the instrument coordinate system, u y and u z They are the components of the satellite-moon vector line in the Y and Z directions in the instrument coordinate system.

[0060] The embodiment of the present invention calculates the scanning field of view angle α and the cold sky field of view angle β by the above two calculation formulas to ensure that the star-moon vector satisfies the constraints of the scanning field of view and the cold sky field of view at the same time.

[0061] Corresponding to the satellite multi-payload monthly prediction method described in the above embodiment, Figure 5 A structural block diagram of a satellite multi-payload monthly forecasting device provided in an embodiment of the present application is shown. For ease of explanation, only the parts related to the embodiment of the present application are shown.

[0062] Reference Figure 5 As shown, the satellite multi-payload monthly forecasting device includes: a coordinate acquisition module 51, a rough calculation module 52 and an optimal solution calculation module 53.

[0063] The coordinate acquisition module 51 is used to obtain the coordinates of the satellite-moon vector connection line in the instrument coordinate system with a preset time accuracy.

[0064] The rough calculation module 52 is used to perform cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints and lunar phase angle constraints on each instrument based on the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument, and obtain the rough time window of the moon entering the field of view corresponding to each instrument.

[0065] The optimal solution calculation module 53 is used to perform a dynamic adaptive golden section extreme value search at preset time intervals based on the rough time window of the moon entering the field of view corresponding to each instrument, calculate the visibility of the moon in the field of view of each instrument, and obtain the optimal observation time of the moon.

[0066] Optionally, the coordinate acquisition module 51 includes: a position acquisition unit, a coordinate system conversion unit, and a star-moon vector calculation unit.

[0067] The position acquisition unit is used to obtain the position information of the satellite, moon, earth and sun in the J2000 geocentric inertial coordinate system based on the simplified perturbation orbit model, combined with the JPL ephemeris and the satellite's two-line orbit elements;

[0068] A coordinate system conversion unit, configured to convert the J2000 geocentric inertial coordinate system into a satellite orbit coordinate system, and then convert the satellite orbit coordinate system into a satellite body coordinate system;

[0069] The satellite-moon vector calculation unit is used to calculate the satellite-moon vector connection line of each device in the instrument coordinate system according to the installation matrix of each device.

[0070] Optionally, the calculation formula for the satellite-moon vector connection line of each device in the instrument coordinate system is: where R body-ins is the transformation matrix from the satellite body coordinate system to the instrument coordinate system, R orb-body is the transformation matrix from the satellite orbit coordinate system to the satellite body coordinate system, R J2000-orb is the transformation matrix from the J2000 geocentric inertial coordinate system to the satellite orbit coordinate system, r moon and r satellite are the positions of the moon and satellite in the J2000 geocentric inertial coordinate system, s represents the distance between the moon and satellite, and u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

[0071] Optionally, the apparatus further includes: an angle calculation module, configured to calculate the cold air field of view angle and the scanning field of view angle of each device according to the circular scanning direction.

[0072] Optionally, the calculation formula for the scanning field angle is: α = 90-arccos(u x / norm(u moon )), where α represents the angle between the satellite moon vector and the YOZ plane of the instrument coordinate system, u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

[0073] Optionally, the calculation formula for the cold sky field of view angle is: Where β represents the angle between the satellite moon vector and the +Y axis of the instrument coordinate system, u y and u z They are respectively the components of the satellite-moon vector line in the Y and Z directions in the instrument coordinate system.

[0074] The device provided by the embodiment of the present invention first narrows the search range through a rough time search to obtain the coordinates of the satellite-moon vector connection line in the instrument coordinate system with rough time accuracy. Based on this, the cold sky field of view angle and the scanning field of view angle are calculated according to its circular scanning direction, and the cold sky field of view range, scanning field of view range and moon phase illumination of each instrument are combined to perform constraints, thereby obtaining a rough time window for the moon to enter the field of view of each instrument. Further, based on the fast search strategy of the dynamic adaptive golden section extreme value search device, the segmentation ratio is dynamically adjusted, the visibility of the moon in the field of view of each instrument is calculated, and the optimal observation time of the moon for each instrument is obtained. The device can realize the rapid and autonomous prediction of the best observation points of the moon by multiple payloads of the FY-3F satellite.

[0075] It can be understood that the present invention constructs a rapid prediction device for lunar observation of multiple payloads of Fengyun-3F based on the combination of rough time search and adaptive golden section extreme value search. By optimizing the calculation of cold sky field of view and scanning field of view angle, a lunar prediction device for cross-orbit circular scanning instruments is proposed, avoiding the limitations of traditional rectangular field of view.

[0076] It should be noted that the information interaction, execution process, etc. between the above-mentioned devices / units / modules are based on the same concept as the method embodiment of this application. Their specific functions and technical effects can be found in the method embodiment section and will not be repeated here.

[0077] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of this application. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, and will not be repeated here.

[0078] An embodiment of the present application also provides a computer device, which includes: at least one processor, a memory, and a computer program stored in the memory and executable on the at least one processor, wherein the processor implements the steps of any of the above-mentioned method embodiments when executing the computer program.

[0079] An embodiment of the present application further provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps in the above-mentioned various method embodiments can be implemented.

[0080] An embodiment of the present application provides a computer program product. When the computer program product is run on a mobile terminal, the mobile terminal can implement the steps in the above-mentioned various method embodiments when executing the computer program product.

[0081] Figure 6 This is a schematic diagram of the structure of a computer device provided in one embodiment of the present application. Figure 6 As shown, the computer device of this embodiment includes: at least one processor 20 ( Figure 6 Only one is shown), a memory 21 and a computer program 22 stored in the memory 21 and executable on the at least one processor 20, wherein the processor 20 implements the steps of any of the above-mentioned visual programming method embodiments when executing the computer program 22.

[0082] The computer device may include, but is not limited to, a processor 20 and a memory 21. Those skilled in the art will understand that Figure 6The computer device is merely an example and does not constitute a limitation on the computer device. The computer device may include more or fewer components than shown in the figure, or a combination of certain components, or different components. For example, the computer device may also include input and output devices, network access devices, etc.

[0083] The processor 20 may be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. A general-purpose processor may be a microprocessor or any conventional processor.

[0084] In some embodiments, the memory 21 may be an internal storage unit of the computer device, such as a hard disk or memory of the computer device. In other embodiments, the memory 21 may also be an external storage device of the computer device, such as a plug-in hard disk equipped on the computer device, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, a flash card (Flash Card), etc. Furthermore, the memory 21 may also include both an internal storage unit of the computer device and an external storage device. The memory 21 is used to store an operating system, an application program, a boot loader (BootLoader), data, and other programs, such as the program code of the computer program. The memory 21 may also be used to temporarily store data that has been output or is to be output.

[0085] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the present application implements all or part of the processes in the above-mentioned embodiment method, which can be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and when the computer program is executed by the processor, it can implement the steps of the above-mentioned various method embodiments. Wherein, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may at least include: any entity or device capable of carrying the computer program code to the device / computer device, a recording medium, a computer memory, a read-only memory (ROM), a random access memory (RAM), an electric carrier signal, a telecommunication signal and a software distribution medium. For example, a USB flash drive, a mobile hard disk, a magnetic disk or an optical disk. In some jurisdictions, according to legislation and patent practice, a computer-readable medium cannot be an electric carrier signal or a telecommunication signal.

[0086] In the above embodiments, the description of each embodiment has its own focus. For parts that are not described or recorded in detail in a certain embodiment, reference can be made to the relevant description of other embodiments.

[0087] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0088] In the embodiments provided in this application, it should be understood that the disclosed apparatus / computer equipment and methods can be implemented in other ways. For example, the apparatus / computer equipment embodiments described above are merely schematic. For example, the division of the modules or units is merely a logical function division. In actual implementation, there may be other division methods, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of the apparatus or unit, which can be electrical, mechanical or other forms.

[0089] The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed across multiple network units. Some or all of these units may be selected to achieve the purpose of this embodiment according to actual needs.

[0090] The above-described embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present application, and should all be included in the scope of protection of the present application.

Claims

1. A satellite multi-payload monthly forecast method, characterized in that: include: Get the coordinates of the satellite-moon vector line in the instrument coordinate system at the preset time accuracy; Based on the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument, each instrument is constrained by cold sky field of view, scanning field of view, Earth night side observation constraint and lunar phase angle, and the rough time window of the moon entering the field of view corresponding to each instrument is obtained. Based on the rough time window of the moon entering the field of view corresponding to each instrument, a dynamic adaptive golden section extreme value search is performed at preset time intervals to calculate the visibility of the moon in the field of view of each instrument and obtain the optimal observation time of the moon.

2. The method according to claim 1, characterized in that The step of obtaining the coordinates of the satellite-moon vector line in the instrument coordinate system at a preset time accuracy includes: Based on the simplified perturbation orbit model, combined with the JPL ephemeris and two-line orbital elements of the satellite, the position information of the satellite, the moon, the earth and the sun in the J2000 geocentric inertial coordinate system is obtained; Converting the J2000 geocentric inertial coordinate system into a satellite orbit coordinate system, and then converting the satellite orbit coordinate system into a satellite body coordinate system; According to the installation matrix of each device, the satellite-moon vector connection line of each device in the instrument coordinate system is calculated.

3. The method according to claim 2, characterized in that The calculation formula of the satellite-moon vector connection line of each device in the instrument coordinate system is: where R body-ins is the transformation matrix from the satellite body coordinate system to the instrument coordinate system, R orb-body is the transformation matrix from the satellite orbit coordinate system to the satellite body coordinate system, R J2000-orb is the transformation matrix from the J2000 geocentric inertial coordinate system to the satellite orbit coordinate system, r moon and r satellite are the positions of the moon and satellite in the J2000 geocentric inertial coordinate system, s represents the distance between the moon and satellite, and u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

4. The method according to claim 1, wherein Before the cold sky field of view angle, scanning field of view angle and lunar phase illumination of each instrument are respectively subjected to cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints and lunar phase angle constraints, and a rough time window for the moon to enter the field of view corresponding to each instrument is obtained, the method also includes: calculating the cold sky field of view angle and scanning field of view angle of each device according to the circular scanning direction.

5. The method according to claim 4, characterized in that The calculation formula of the scanning field angle is: α=90-arccos(u x / norm(u moon )), where α represents the angle between the satellite moon vector and the YOZ plane of the instrument coordinate system, u moon represents the satellite-moon vector line in the instrument coordinate system, u x ,u y ,u z u moon Components in the XYZ directions.

6. The method according to claim 4, characterized in that The calculation formula of the cold sky viewing angle is: Where β represents the angle between the satellite moon vector and the +Y axis of the instrument coordinate system, u y and u z They are respectively the components of the satellite-moon vector line in the Y and Z directions in the instrument coordinate system.

7. A satellite multi-payload lunar forecasting device, characterized in that: include: Coordinate acquisition module, rough calculation module and optimal solution calculation module; The coordinate acquisition module is used to obtain the coordinates of the satellite-moon vector connection line in the instrument coordinate system at a preset time accuracy; The rough calculation module is used to perform cold sky field of view constraints, scanning field of view constraints, Earth night side observation constraints, and lunar phase angle constraints on each instrument based on the cold sky field of view angle, scanning field of view angle, and lunar phase illumination of each instrument, and obtain a rough time window for the moon to enter the field of view corresponding to each instrument; The optimal solution calculation module is used to perform dynamic adaptive golden section extreme value search at preset time intervals based on the rough time window of the moon entering the field of view corresponding to each instrument, calculate the visibility of the moon in the field of view of each instrument, and obtain the optimal observation time of the moon.

8. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the method according to any one of claims 1 to 6 is implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method according to any one of claims 1 to 6 is performed.

10. A computer program product, characterized in that When the computer program product is run on a computer device, the computer device is caused to perform the method according to any one of claims 1 to 6.

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