Satellite coverage area observation method, system, equipment and medium

Abstract

The invention relates to the technical field of spacecraft observation, provides an observation method, system and equipment for a satellite coverage area and a medium, and solves the technical problem of how to improve the quality of satellite observation area data in the prior art. The method comprises the following steps: acquiring initial stripe information for dividing a satellite coverage area according to a satellite observation task requirement; initial circle information of the satellite passing through each divided strip is calculated; calculating a swing measurement angle between each strip and the satellite; calculating the on-off time of the satellite passing through the strip according to the local time of the satellite passing through the descending node of the strip and the elevation angle of the sun at the central point of the strip; screening out final circle information capable of executing a satellite observation task from the initial circle information according to the swing measurement angle between each strip and the satellite and the on-off time when the satellite passes through the strip; and outputting the coverage area of each strip in the satellite coverage area, the total coverage area of all the strips and the coverage proportion according to the final circle information.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft observation technology, and in particular to a method, system, equipment and medium for observing a satellite coverage area. Background Art

[0002] With the rapid development of global aerospace technology and the increasing maturity of remote sensing technology, satellite regional observation has become an important support means in the fields of modern scientific research, national defense security, meteorological monitoring, monitoring of marine resources, disaster warning and environmental protection, intelligent agriculture, and smart city construction. Satellite regional observation coverage refers to the use of high-precision remote sensing satellites to observe designated geographical areas in real time and continuously to obtain various key data to meet the needs of ground monitoring, scientific analysis, and decision support. The realization of satellite observation regional coverage depends on precise orbit design, powerful satellite perception capabilities, and advanced communication technology. Through different types of remote sensing satellite systems (such as optical remote sensing, radar remote sensing, infrared remote sensing, etc.), multi-dimensional and multi-time comprehensive observations are carried out to form a comprehensive data network. These satellites can flexibly adjust the observation range and frequency according to mission requirements, monitor the changes in the surface in real time, and provide solid data support for accurate regional analysis, event response, and prediction decisions.

[0003] When calculating the strips of satellite coverage of a geographic area, existing calculation models may ignore some key variables or dynamic changes, resulting in deviations between the calculation results and the actual situation. In addition, a large amount of incorrect or redundant information is generated during the processing of satellite data. These redundant data may not contribute substantial value in practical applications, but instead increase the complexity of data processing. The results of the analytical calculations cannot adjust the measured pendulum angle of the satellite payload, resulting in the calculation results covering an area that is too small, and more satellite orbits are required to cover the geographic area. Summary of the invention

[0004] The purpose of the present invention is to provide a method, system, device and medium for observing a satellite coverage area, so as to solve the technical problem of how to improve the quality of satellite observation area data in the prior art.

[0005] To solve the above technical problems, as one aspect of the present invention, a method for observing a satellite coverage area is provided, comprising the following steps:

[0006] According to the satellite observation mission requirements, obtain the initial strip information for dividing the satellite coverage area;

[0007] Calculate the initial circle information of the satellite passing through each divided strip; wherein the initial circle information includes the width, starting position, coverage circle number and total coverage number of each strip;

[0008] Calculate the pendulum angle between each strip and the satellite;

[0009] The on / off time of the satellite passing through the strip is calculated based on the local time of the descending node of the strip and the altitude angle of the sun at the center of the strip;

[0010] According to the measured pendulum angle between each strip and the satellite and the on / off time of the satellite passing through the strip, the final circle information that can perform the satellite observation mission is selected from the initial circle information;

[0011] According to the final circle information, the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio are output.

[0012] Further, the satellite observation mission requirement includes the input satellite orbit height, satellite field of view angle, and width of the area that the satellite needs to cover; the obtaining of initial strip information for dividing the satellite coverage area according to the satellite observation mission requirement includes:

[0013] Calculate the ground width covered by the satellite based on the input satellite orbit altitude and satellite field of view angle;

[0014] Calculate the required number of strips according to the ground width covered by the satellite and the input width of the area that the satellite needs to cover;

[0015] According to the calculated number of strips and ground width, the area that the satellite needs to cover is divided into a number of strips; wherein the width of each strip is the difference between the width of the area that the satellite needs to cover and the number of strips;

[0016] Output initial stripe information; wherein the initial stripe information includes the number of stripes and the width of each stripe.

[0017] Furthermore, the satellite observation task requirement also includes an input satellite orbit period and a satellite shooting time interval; the calculation of the initial circle information of the satellite passing through each divided strip includes:

[0018] Calculate the starting position of each strip according to the ground width and the number of strips covered by the satellite;

[0019] The coverage circles of each strip are calculated based on the input satellite orbit period and satellite shooting time interval;

[0020] According to the coverage times of the strips, the total coverage times of each strip in a specific time period is calculated;

[0021] Output the initial circle information of the strip.

[0022] Further, the calculating of the pendulum angle between each strip and the satellite includes:

[0023] According to the orbital parameters of the satellite, the coordinates of the center point of each strip are calculated;

[0024] Calculate the distance between the center point of each strip and the subsatellite point;

[0025] According to the distance between the center point of each strip and the subsatellite point, the pendulum angle between each strip and the satellite is calculated.

[0026] Further, the method of calculating the on / off time of the satellite passing through the strip according to the solar angle and the descending node local time includes:

[0027] According to the local time of the descending node of the satellite passing through the strip and the satellite orbit period, the time when the satellite will pass through the strip next time is calculated;

[0028] Calculate the altitude angle of the sun at the center point of the strip;

[0029] According to the altitude angle of the sun at the center of the strip and the minimum altitude angle of the sun required when the satellite is turned on, the time when the satellite passes through the strip is determined.

[0030] Furthermore, the final circle information capable of performing the satellite observation mission is selected from the initial circle information according to the measured pendulum angle between each strip and the satellite and the power-on and power-off time of the satellite passing through the strip, including:

[0031] Compare the measured pendulum angle between the strip and the satellite with the maximum measured pendulum angle of the satellite sensor;

[0032] Confirm that the pendulum angle between the strip in the final circle information and the satellite does not exceed the maximum pendulum angle of the satellite sensor;

[0033] Confirm that the satellite corresponding to the strip in the final circle information is in the power-on time.

[0034] Furthermore, the output of the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio according to the final circle information includes:

[0035] Calculate the boundary of each strip based on the center point and width of each strip;

[0036] Drawing stripe information of each round in the final round information, wherein the stripe information includes a stripe boundary and a coverage area;

[0037] According to the radius of the earth, the latitude range of each strip and the boundary of each strip, the coverage area of ​​each strip, the total coverage area of ​​all strips and the coverage ratio are calculated;

[0038] Output the drawn strip information and calculation results.

[0039] As a second aspect of the present invention, there is provided an observation system for a satellite coverage area, comprising:

[0040] An acquisition module is used to obtain initial strip information for dividing the satellite coverage area according to the satellite observation mission requirements;

[0041] The first calculation module is used to calculate the initial circle information of the satellite passing through each divided strip; wherein the initial circle information includes the width, starting position, coverage circle and total coverage number of each strip

[0042] The second calculation module is used to calculate the pendulum angle between each strip and the satellite;

[0043] The third calculation module is used to calculate the power on / off time of the satellite passing through the strip according to the local time of the descending node of the strip and the altitude angle of the sun at the center of the strip;

[0044] A screening module is used to screen out the final circle information that can perform the satellite observation mission from the initial circle information according to the measured pendulum angle between each strip and the satellite and the power-on and power-off time of the satellite passing through the strip;

[0045] The output module is used to output the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio according to the final circle information.

[0046] As a third aspect of the present invention, there is provided an electronic device, comprising:

[0047] one or more processors;

[0048] A storage device for storing one or more programs;

[0049] When the one or more programs are executed by the one or more processors, the one or more processors implement the method described in the first aspect above.

[0050] As a fourth aspect of the present invention, a computer-readable medium is provided, on which a computer program is stored, and when the program is executed by a processor, the method described in the first aspect is implemented.

[0051] The beneficial effects of the present invention are:

[0052] The present invention divides the coverage area into several strips, calculates the initial circle information of the satellite passing through each divided strip, and adds filtering conditions such as the solar altitude angle, the local time of the descending node and the pendulum angle to screen out the satellite revisit circles to reduce the calculation error. The present invention solves the technical problem of how to improve the quality of satellite observation area data in the prior art, provides more reliable information support for decision-making, and can monitor specific areas at a higher frequency, so as to obtain various types of ground and ocean data in real time. This is particularly important for fields such as weather forecasting, environmental monitoring and disaster warning, so that decision makers can grasp real-time information and take countermeasures at the first time. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 A step diagram of a method for observing a satellite coverage area is schematically shown.

[0054] Figure 2 A block diagram of an observation system for a satellite coverage area is schematically shown.

[0055] Figure 3 A block diagram of an electronic device is schematically shown.

[0056] Figure 4 A block diagram of a computer-readable medium is schematically shown. DETAILED DESCRIPTION

[0057] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this application will be comprehensive and complete and will fully convey the concepts of the example embodiments to those skilled in the art. The same reference numerals in the figures represent the same or similar parts, and thus their repeated description will be omitted.

[0058] In addition, described feature, structure or characteristic can be combined in one or more embodiments in any suitable manner. In the following description, many specific details are provided to provide a full understanding of the embodiments of the present application. However, those skilled in the art will appreciate that the technical scheme of the present application can be put into practice without one or more of the specific details, or other methods, components, devices, steps, etc. can be adopted. In other cases, known methods, devices, realizations or operations are not shown or described in detail to avoid blurring the various aspects of the application.

[0059] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities may be implemented in software form, or in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0060] The flowcharts shown in the accompanying drawings are only exemplary and do not necessarily include all the contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps can be decomposed, and some operations / steps can be combined or partially combined, so the actual execution order may change according to actual conditions.

[0061] It should be understood that although the terms first, second, third, etc. may be used herein to describe various components, these components should not be limited by these terms. These terms are used to distinguish one component from another component. Therefore, the first component discussed below can be referred to as the second component without departing from the teachings of the concepts of the present application. As used herein, the term "and / or" includes any one of the associated listed items and all combinations of one or more.

[0062] Below, some terms in the embodiments of the present application are explained to facilitate understanding by those skilled in the art.

[0063] 1) Descending Node Local Time: The descending node is one of the satellite orbit parameters. When a satellite moves from north to south, the intersection of the great circle where its orbital plane is located and the equatorial plane is called the descending node. When a satellite flies from the North Pole to the South Pole and crosses the equator, the local time of the geographical location corresponding to the subsatellite point is called the descending node local time.

[0064] The position of a sun-synchronous satellite relative to the sun remains unchanged. Relative to the earth, affected by the earth's non-spherical gravitational field, the rate of change of the right ascension of its ascending node is the same as the angular velocity of the sun's rotation relative to the earth's center. Therefore, in theory, the local time of the same sun-synchronous satellite at any point in the orbit is unchanged, but various perturbations will cause time drift. Since the satellite is in a sun-synchronous orbit, once the local time of the satellite's descending node is determined, the relationship between sunlight and the satellite is basically determined, and it will only make a large-cycle round-trip motion with seasonal changes.

[0065] 2) Satellite payload roll angle: The roll angle is the horizontal offset angle of the satellite sensor relative to the ground. When the roll angle is 0°, the satellite's sensor shoots the ground vertically, and as the roll angle increases, the sensor will deviate from the vertical position. High roll angles usually lead to a decrease in image quality because it introduces a certain perspective effect and deformation. Therefore, the roll angle should not be greater than 30° to ensure that the image maintains a high quality.

[0066] Although a smaller roll angle is generally beneficial to the quality of high-resolution images, it also affects the satellite's revisit efficiency. Revisit efficiency refers to the satellite's ability to regularly collect the same area. Large-angle image acquisition (roll angle less than or equal to 20°) will reduce the number of times the satellite attempts to collect images in a certain period of time, which may result in a reduced chance of successfully collecting images in some cases. Therefore, when choosing a shooting angle, it is necessary to strike a balance between high-quality images and revisit efficiency.

[0067] Those skilled in the art will appreciate that the drawings are merely schematic diagrams of example embodiments, and the modules or processes in the drawings are not necessarily necessary for implementing the present application, and therefore cannot be used to limit the scope of protection of the present application.

[0068] According to the first specific embodiment of the present invention, Figure 1 As shown, the present invention provides a method for observing a satellite coverage area, comprising the following steps:

[0069] S11, according to the satellite observation mission requirements, obtain initial strip information for dividing the satellite coverage area.

[0070] The division of satellite coverage areas into strips is mainly to divide an area into several strips (strip coverage areas) for better data processing, analysis and visualization. These strips can be equally spaced or divided according to certain specific rules or requirements.

[0071] Among them, the corresponding parameters can be input according to the satellite observation mission requirements, including but not limited to:

[0072] Satellite orbit altitude (H): The height of the satellite from the ground, affecting the ground area covered;

[0073] Satellite field of view (FOV): The field of view of the satellite sensor determines the ground area that can be covered in each shot;

[0074] Geographic area: The width of the area (W) that the satellite needs to cover, which can be represented by a polygon or rectangle.

[0075] Specifically, step S11 may include the following steps:

[0076] S111, calculating the ground width covered by the satellite according to the input satellite orbit altitude and satellite field of view angle.

[0077] First, we can use trigonometric functions and geometry to calculate the width of the ground that a satellite can cover at a specific altitude at one time using the following formula:

[0078]

[0079] Where D is the width of the ground that the satellite can cover at one time.

[0080] S112, calculating the required number of strips according to the ground width covered by the satellite and the input width of the area that the satellite needs to cover.

[0081] Based on the width of the area to be covered (W) and the width of the ground that the satellite can cover at one time (D), the number of strips required can be calculated using the following formula:

[0082]

[0083] Where N is the number of stripes, Indicates rounding up.

[0084] S113: Divide the area to be covered by the satellite into a plurality of strips according to the calculated number of strips and ground width.

[0085] The width of each stripe is the difference between the width of the area that the satellite needs to cover and the number of stripes. The width of each stripe (Wb) is W / N.

[0086] S114, output initial stripe information.

[0087] The initial strip information includes the number of strips and the width of each strip. For each strip, check whether it completely covers the specified area to ensure that there is no missing part. If the boundary of the strip fails to meet the coverage requirements, the width of the strip in the coverage area and the number of strips can be dynamically adjusted by dynamically adjusting the payload capacity of the satellite. Finally, the divided strip information is output, including the starting point and end point of each strip, as well as the coverage of each strip. The center point, starting point, and end point of the strip can be obtained based on the calculated rectangular strip. And, according to the coverage of each strip, the coverage ratio of the strip covering the specified area is calculated.

[0088] After the initial stripe information is obtained, step S12 is executed.

[0089] S12, calculating the initial circle information of the satellite passing through each divided strip.

[0090] The initial circle information includes the width, starting position, number of coverage circles and total number of coverage of each strip. When the satellite passes through a specific area, the number of coverage circles of each strip is calculated. This involves factors such as satellite orbit, strip division and time interval of satellite shooting. The parameters required in this step include but are not limited to:

[0091] Satellite orbit altitude (H): The height of the satellite from the ground, affecting the ground area covered;

[0092] Satellite field of view (FOV): The field of view of the satellite sensor determines the ground area that can be covered in each shot;

[0093] Number of stripes (N): the number of stripes used to divide the area;

[0094] Strip width (Wb): the width of each strip;

[0095] Satellite orbit period (T): the time required for a satellite to complete one orbital cycle;

[0096] Satellite shooting time interval (Δt): the time interval between each satellite shooting.

[0097] Specifically, step S12 may include the following steps:

[0098] S121, calculating the starting position of each strip according to the ground width covered by the satellite and the number of strips.

[0099] The starting position of each stripe can be calculated according to the stripe width (Wb) and the number of stripes (N) by the following formula:

[0100] Starting position i =i×W b (i=0,1,2,…,N-1)

[0101] S122, calculating the number of coverage circles of each strip according to the input satellite orbit period and satellite shooting time interval.

[0102] Each time the satellite passes through an orbital cycle, it will cover the area. The number of times each strip is covered in a complete orbital cycle can be calculated using the following formula:

[0103]

[0104] S123, calculating the total number of coverage times of each stripe in a specific time period according to the number of coverage circles of the stripe.

[0105] The total number of coverages for each stripe in a specific time period can be calculated using the following formula:

[0106] Total coverage i = laps i ×Number of time periods

[0107] S124, output the initial circle information of the strip.

[0108] The final output records the initial stripe loop information, including the starting position, loop number and total coverage times of each stripe.

[0109] After obtaining the initial round information, execute step S13.

[0110] S13, calculating the pendulum angle between each strip and the satellite.

[0111] In satellite remote sensing and ground cover monitoring, it is very important to know whether the satellite's pendulum angle exceeds its pendulum capability. Pendulum refers to the deviation angle of the sensor relative to the satellite's main axis during the satellite's orbit. This application needs to calculate the pendulum angle between the satellite and the strip and compare it with the satellite's pendulum capability to determine whether it exceeds the satellite's pendulum capability.

[0112] The parameters required in this step include but are not limited to:

[0113] Satellite orbit altitude (H): The height of the satellite from the ground, affecting the ground area covered;

[0114] Number of stripes (N): the number of stripes used to divide the area;

[0115] Strip center point coordinates: the center point coordinates of each strip (latitude and longitude);

[0116] Satellite subsatellite point coordinates: the subsatellite point coordinates (latitude and longitude) of the satellite at a specific time;

[0117] Satellite pendulum measurement capability (θ_max): The maximum pendulum measurement angle of the satellite sensor (radians or degrees).

[0118] Optionally, step S13 may include the following steps:

[0119] S131, calculating the coordinates of the center point of each strip according to the orbital parameters of the satellite.

[0120] First, convert the latitude and longitude to radians:

[0121]

[0122] Among them, lat 1 ,lat 2 are the latitudes of the strip’s starting and ending points, respectively, lon 1 ,lon 2 is the longitude of the strip start and strip end.

[0123] Next, calculate the longitude lon of the center point mid and latitude lat mid :

[0124] B x = cos(lat 2 )·cos(lon 2 )

[0125] B y = cos(lat2 )·sin(lon 2 )

[0126] A x = cos(lat 1 )·cos(lon 1 )

[0127] A y = cos(lat 1 )·sin(lon 1 )

[0128] C x =A x +B x

[0129] C y =A y +B y

[0130] lat mid =arctan2(C y ,C x )

[0131] lon mid =arctan2(B y +A y ,B x +A x )

[0132] Among them, A x , A y refers to the x,y coordinate value of the starting point of the strip, B x , B y refers to the x,y value of the end point of the strip, C x , C y It refers to the sum of the x-coordinate of the strip's starting point and the x-coordinate of the strip's end point, as well as the sum of the y-coordinate of the starting point and the y-coordinate of the end point.

[0133] S132, calculating the distance between the center point of each strip and the sub-satellite point.

[0134] The distance d between the satellite's subsatellite point and the center point of each strip can be calculated using the Haversine formula:

[0135]

[0136] Where R is the radius of the earth (about 6371km), △lat is the latitude of the center point of the strip minus the latitude of the subsatellite point, and △lon is the longitude of the center point of the strip minus the longitude of the subsatellite point. Lat1 and lat2 are the latitude values ​​of the two points.

[0137] S133, calculating the pendulum angle between each strip and the satellite according to the distance between the center point of each strip and the sub-satellite point of the satellite.

[0138] The pendulum angle between each strip and the satellite can be calculated by the following formula:

[0139]

[0140] Where: θ is the pendulum angle between the strip and the satellite, d is the horizontal distance between the strip center and the subsatellite point, and H is the orbital altitude of the satellite.

[0141] S14, calculating the power on and off time of the satellite passing through the strip according to the local time of the descending node of the strip and the altitude angle of the sun at the center of the strip.

[0142] In order to filter out the on / off time of the satellite passing through the strip based on the sun angle and the local time of the descending node, it is necessary to consider the impact of the sun angle on satellite observation and the intersection time of the satellite orbit with the ground. The parameters required in this step include but are not limited to:

[0143] Strip center point coordinates: the center point coordinates of each strip (latitude and longitude);

[0144] Descending Node Local Time (DPT): The local time when the satellite passes through the descending node of the strip;

[0145] Satellite orbit period (T): the time required for a satellite to complete one orbital cycle;

[0146] Sun altitude (SH): the altitude of the sun at the center of the strip;

[0147] Power-on threshold (SH_min): The minimum solar altitude angle required for the satellite to be powered on.

[0148] Optionally, step S14 may include the following steps:

[0149] S141, calculating the time when the satellite will pass through the strip next time according to the local time of the descending node of the strip when the satellite passes through the strip and the satellite orbit period.

[0150] Assuming that the satellite's orbit is regular, the time when the satellite will next pass through the strip can be calculated using the local time of the descending node and the orbital period. The formula is as follows:

[0151] Next elapsed time = DPT + n × T

[0152] S142, calculate the altitude angle of the sun at the center point of the strip.

[0153] The solar altitude angle can be calculated using the following formula:

[0154] SH = arcsin (sin (latitude) sin (solar declination) + cos (latitude) cos (solar declination) cos (hour angle))

[0155] The hour angle can be calculated by the following formula:

[0156] Hour angle = 15°×(local time - 12)

[0157] S143, confirming the power on and off time of the satellite passing through the strip according to the altitude angle of the sun at the center point of the strip and the minimum altitude angle of the sun required when the satellite is powered on.

[0158] The satellite power-on time refers to the time when the solar altitude angle reaches the power-on threshold. It is necessary to calculate the solar altitude angle at different time points and determine whether it exceeds the power-on threshold.

[0159] According to the altitude angle of the sun at the center of the strip, the power-on threshold is set to 0, which can simply determine day and night:

[0160]

[0161] Where H is the altitude angle of the sun at the center of the strip.

[0162] The satellite is powered on during the day and powered off during the night. Therefore, if the solar altitude angle corresponding to a certain strip is greater than 0, the satellite is powered on and the circle corresponding to the strip should be retained. If the solar altitude angle corresponding to a certain strip is not greater than 0, the satellite is powered off and the circle corresponding to the strip is not retained.

[0163] After obtaining the pendulum angle between the strip and the satellite and the on / off time of the satellite passing through the strip, step S15 is executed.

[0164] S15, based on the measured pendulum angle between each strip and the satellite and the on / off time of the satellite passing through the strip, the final circle information capable of executing the satellite observation mission is filtered out from the initial circle information.

[0165] Optionally, step S15 may include the following steps:

[0166] S151, comparing the measured pendulum angle between the strip and the satellite with the maximum measured pendulum angle of the satellite sensor.

[0167] S152, confirming that the pendulum angle between the strip in the final circle information and the satellite does not exceed the maximum pendulum angle of the satellite sensor.

[0168] By comparing the calculated pendulum angle with the satellite's pendulum measurement capability, it is indicated whether it exceeds the satellite's pendulum measurement capability. If the pendulum measurement angle of a strip exceeds the satellite's pendulum measurement capability, the circle corresponding to the strip will not be used, that is, the pendulum measurement angle between the strip and the satellite in the final circle information does not exceed the maximum pendulum measurement angle of the satellite sensor.

[0169] S153, confirming that the satellite corresponding to the strip in the final circle information is in the power-on time.

[0170] S16, outputting the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips, and the coverage ratio according to the final circle information.

[0171] Based on the satellite's field of view and the information of the number of circles, the strip information of the area where the satellite passes can be drawn. The principles of geometry and trigonometry can be used to calculate the ground area covered by the satellite at different circles. Here, it is necessary to calculate the strip areas covered by the satellite's field of view at different circles, draw the boundaries of these areas, and then integrate the coverage area of ​​each strip, and calculate the total coverage area based on the boundaries of the strips.

[0172] The parameters required in this step include but are not limited to:

[0173] Satellite orbit altitude (H): The altitude of the satellite from the ground.

[0174] Field of view (FOV): The field of view of the satellite sensor (usually in radians or degrees);

[0175] Descending Node Local Time (DPT): The local time when the satellite passes through the descending node of the strip;

[0176] Orbital period (T): the time required for a satellite to complete one orbital cycle;

[0177] Number of stripes (N): the number of stripes to be calculated;

[0178] Strip width (W): The width of each strip, which can usually be calculated based on the field of view angle;

[0179] Strip information: the left and right boundaries of each strip and the corresponding longitude and latitude range;

[0180] Region of interest: defines a rectangular or polygonal area representing the ground area that needs attention;

[0181] Earth's surface area: This can be calculated using the Earth's radius.

[0182] Optionally, step S16 may include the following steps:

[0183] S161, calculating the boundary of each stripe according to the center point and width of each stripe.

[0184] First, we can calculate the center point of each stripe according to the orbital parameters of the satellite. Assuming that the stripes are evenly distributed, we can use the following formula to get the center point of the stripe:

[0185] Strip center point i = longitude of descending node + i × W

[0186] Among them, W can be calculated by the field of view angle:

[0187]

[0188] Next, calculate the stripe boundaries. The boundaries of each stripe can be calculated by the stripe center point and half width (i.e., field of view radius). Assuming the stripe width is W, the boundaries can be expressed as:

[0189]

[0190]

[0191] S162, drawing the stripe information of each round in the final round information, wherein the stripe information includes a stripe boundary and a coverage area.

[0192] Based on the orbital period and circle information, draw the strip information of each circle. You can use a loop to traverse each circle and calculate the corresponding strip boundaries.

[0193] S163, calculating the coverage area of ​​each strip, the total coverage area of ​​all strips, and the coverage ratio according to the radius of the earth, the latitude range of each strip, and the boundary of each strip.

[0194] First, the coverage area of ​​each strip can be calculated by the following formula:

[0195] Coverage area = (right boundary - left boundary) × latitude range × R 2

[0196] Here, R is the radius of the Earth (about 6371 km), and the latitudinal extent of the strip is assumed to be constant.

[0197] Next, summarize the coverage area of ​​all strips, the formula is as follows:

[0198]

[0199] Then, calculate the coverage ratio, which can be calculated by the following formula:

[0200]

[0201] The area of ​​the region of interest can be determined by simple rectangle calculation or more complex polygon calculation.

[0202] S164, outputting the drawn strip information and calculation results.

[0203] This application divides the coverage area into several strips, calculates the initial circle information of the satellite passing through each divided strip, and adds filtering conditions such as the solar altitude angle, the local time of the descending node, and the pendulum angle to screen out the satellite revisit circles to reduce the calculation error. It solves the technical problem of how to improve the quality of satellite observation area data in the existing technology, provides more reliable information support for decision-making, and can monitor specific areas at a higher frequency, so as to obtain various types of ground and ocean data in real time. This is especially important for fields such as weather forecasting, environmental monitoring and disaster warning, so that decision makers can grasp real-time information and take countermeasures at the first time.

[0204] According to a second specific embodiment of the present invention, the present invention provides an observation system for a satellite coverage area, using the method of the first specific embodiment, such as Figure 2 As shown, the observation system 400 of the satellite coverage area includes:

[0205] The acquisition module 410 is used to acquire initial strip information for dividing the satellite coverage area according to the satellite observation task requirements;

[0206] The first calculation module 420 is used to calculate the initial circle information of the satellite passing through each divided strip; wherein the initial circle information includes the width, starting position, coverage circle number and total coverage number of each strip

[0207] The second calculation module 430 is used to calculate the pendulum angle between each strip and the satellite;

[0208] The third calculation module 440 is used to calculate the power on / off time of the satellite passing through the strip according to the local time of the descending node of the strip and the altitude angle of the sun at the center of the strip;

[0209] A screening module 450 is used to screen out final circle information capable of performing satellite observation tasks from the initial circle information according to the pendulum angle between each strip and the satellite and the on / off time of the satellite passing through the strip;

[0210] The output module 460 is used to output the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio according to the final circle information.

[0211] According to a third specific embodiment of the present invention, the present invention provides an electronic device, such as Figure 3 As shown, Figure 3It is a block diagram of an electronic device according to an exemplary embodiment.

[0212] Refer to the following Figure 3 The electronic device 200 according to this embodiment of the present application is described. Figure 3 The electronic device 200 shown is merely an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0213] like Figure 3 As shown, the electronic device 200 is in the form of a general computing device. The components of the electronic device 200 may include, but are not limited to: at least one processing unit 210, at least one storage unit 220, a bus 230 connecting different system components (including the storage unit 220 and the processing unit 210), a display unit 240, etc.

[0214] The storage unit stores a program code, which can be executed by the processing unit 210, so that the processing unit 210 performs the steps described in this specification according to various exemplary embodiments of the present application. For example, the processing unit 210 can perform the following steps: Figure 1 Follow the steps shown in .

[0215] The storage unit 220 may include a readable medium in the form of a volatile storage unit, such as a random access memory unit (RAM) 2201 and / or a cache memory unit 2202 , and may further include a read-only memory unit (ROM) 2203 .

[0216] The storage unit 220 may also include a program / utility 2204 having a set (at least one) of program modules 2205, such program modules 2205 including but not limited to: an operating system, one or more application programs, other program modules and program data, each of which or some combination may include the implementation of a network environment.

[0217] Bus 230 may represent one or more of several types of bus structures, including a memory unit bus or memory unit controller, a peripheral bus, an accelerated graphics port, a processing unit, or a local bus using any of a variety of bus architectures.

[0218] The electronic device 200 may also communicate with one or more external devices 200' (e.g., keyboards, pointing devices, Bluetooth devices, etc.) to enable a user to communicate with the electronic device 200, and / or any device (e.g., routers, modems, etc.) that the electronic device 200 can communicate with one or more other computing devices. Such communication may be performed via an input / output (I / O) interface 250. In addition, the electronic device 200 may also communicate with one or more networks (e.g., a local area network (LAN), a wide area network (WAN), and / or a public network, such as the Internet) via a network adapter 260. The network adapter 260 may communicate with other modules of the electronic device 200 via the bus 230. It should be understood that, although not shown in the figure, other hardware and / or software modules may be used in conjunction with the electronic device 200, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0219] Through the description of the above implementations, those skilled in the art can easily understand that the example implementations described here can be implemented by software, or by combining software with necessary hardware.

[0220] Therefore, according to a fourth specific embodiment of the present invention, the present invention provides a computer readable medium. Figure 4 As shown, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, and includes a number of instructions to enable a computing device (which can be a personal computer, a server, or a network device, etc.) to execute the above method according to the embodiment of the present invention.

[0221] The software product may be any combination of one or more readable media. The readable medium may be a readable signal medium or a readable storage medium. The readable storage medium may be, for example, but not limited to, a system, device or component of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination thereof. More specific examples (non-exhaustive list) of readable storage media include: an electrical connection with one or more wires, a portable 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 thereof.

[0222] The computer readable storage medium may include a data signal propagated in a baseband or as part of a carrier wave, wherein a readable program code is carried. This propagated data signal may take a variety of forms, including but not limited to an electromagnetic signal, an optical signal, or any suitable combination of the above. The readable storage medium may also be any readable medium other than a readable storage medium, which may send, propagate, or transmit a program for use by an instruction execution system, an apparatus, or a device or used in combination with it. The program code contained on the readable storage medium may be transmitted with any appropriate medium, including but not limited to wireless, wired, optical cable, RF, etc., or any suitable combination of the above.

[0223] Program code for performing the operations of the present invention may be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java, C++, etc., and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, as a separate software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server. In cases involving a remote computing device, the remote computing device may be connected to the user computing device through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computing device (e.g., through the Internet using an Internet service provider).

[0224] The computer-readable medium carries one or more programs. When the one or more programs are executed by a device, the computer-readable medium implements the functions of the first embodiment.

[0225] Those skilled in the art will appreciate that the above modules can be distributed in the device according to the description of the embodiment, or can be changed accordingly and only used in one or more devices different from the embodiment. The modules of the above embodiments can be combined into one module, or further divided into multiple sub-modules.

[0226] Through the description of the above embodiments, it is easy for those skilled in the art to understand that the example embodiments described here can be implemented by software, or by software combined with necessary hardware. Therefore, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which can be a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the method according to the embodiment of the present invention.

[0227] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for observing a satellite coverage area, characterized in that: The following steps are involved: According to the satellite observation mission requirements, obtain the initial strip information for dividing the satellite coverage area; Calculate the initial circle information of the satellite passing through each divided strip; wherein the initial circle information includes the width, starting position, coverage circle number and total coverage number of each strip; Calculate the pendulum angle between each strip and the satellite; The on / off time of the satellite passing through the strip is calculated based on the local time of the descending node of the strip and the altitude angle of the sun at the center of the strip; According to the measured pendulum angle between each strip and the satellite and the on / off time of the satellite passing through the strip, the final circle information that can perform the satellite observation mission is selected from the initial circle information; According to the final circle information, the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio are output.

2. The method for observing the satellite coverage area according to claim 1, characterized in that: in, The satellite observation mission requirements include the input satellite orbit altitude, satellite field of view angle, and the width of the area that the satellite needs to cover; The obtaining of initial strip information for dividing the satellite coverage area according to the satellite observation mission requirements includes: Calculate the ground width covered by the satellite based on the input satellite orbit altitude and satellite field of view angle; Calculate the required number of strips according to the ground width covered by the satellite and the input width of the area that the satellite needs to cover; According to the calculated number of strips and ground width, the area that the satellite needs to cover is divided into a number of strips; wherein the width of each strip is the difference between the width of the area that the satellite needs to cover and the number of strips; Output initial stripe information; wherein the initial stripe information includes the number of stripes and the width of each stripe.

3. The method for observing the satellite coverage area according to claim 2, characterized in that: in, The satellite observation task requirement also includes the input satellite orbit period and satellite shooting time interval; the calculation of the initial circle information of the satellite passing through each divided strip includes: Calculate the starting position of each strip according to the ground width and the number of strips covered by the satellite; The coverage circles of each strip are calculated based on the input satellite orbit period and satellite shooting time interval; According to the coverage times of the strips, the total coverage times of each strip in a specific time period is calculated; Output the initial circle information of the strip.

4. The method for observing the satellite coverage area according to claim 3, characterized in that: The step of calculating the pendulum angle between each strip and the satellite comprises: According to the orbital parameters of the satellite, the coordinates of the center point of each strip are calculated; Calculate the distance between the center point of each strip and the subsatellite point; According to the distance between the center point of each strip and the subsatellite point, the pendulum angle between each strip and the satellite is calculated.

5. The method for observing the satellite coverage area according to claim 4, characterized in that: The method of calculating the on / off time of the satellite passing through the strip according to the solar angle and the local time of the descending node includes: According to the local time of the descending node of the satellite passing through the strip and the satellite orbit period, the time when the satellite will pass through the strip next time is calculated; Calculate the altitude angle of the sun at the center point of the strip; According to the altitude angle of the sun at the center of the strip and the minimum altitude angle of the sun required when the satellite is turned on, the time when the satellite passes through the strip is determined.

6. The method for observing the satellite coverage area according to claim 5, characterized in that: The method of filtering out the final circle information capable of performing the satellite observation mission from the initial circle information according to the pendulum angle between each strip and the satellite and the on / off time of the satellite passing through the strip includes: Compare the measured pendulum angle between the strip and the satellite with the maximum measured pendulum angle of the satellite sensor; Confirm that the pendulum angle between the strip in the final circle information and the satellite does not exceed the maximum pendulum angle of the satellite sensor; Confirm that the satellite corresponding to the strip in the final circle information is in the power-on time.

7. The method for observing the satellite coverage area according to claim 6, characterized in that: The output of the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio according to the final circle information includes: Calculate the boundary of each strip based on the center point and width of each strip; Drawing stripe information of each round in the final round information, wherein the stripe information includes a stripe boundary and a coverage area; According to the radius of the earth, the latitude range of each strip and the boundary of each strip, the coverage area of ​​each strip, the total coverage area of ​​all strips and the coverage ratio are calculated; Output the drawn strip information and calculation results.

8. An observation system for a satellite coverage area, characterized in that: include: An acquisition module is used to obtain initial strip information for dividing the satellite coverage area according to the satellite observation mission requirements; The first calculation module is used to calculate the initial circle information of the satellite passing through each divided strip; wherein the initial circle information includes the width, starting position, coverage circle and total coverage number of each strip The second calculation module is used to calculate the pendulum angle between each strip and the satellite; The third calculation module is used to calculate the power on / off time of the satellite passing through the strip according to the local time of the descending node of the strip and the altitude angle of the sun at the center of the strip; A screening module is used to screen out the final circle information that can perform the satellite observation mission from the initial circle information according to the measured pendulum angle between each strip and the satellite and the power-on and power-off time of the satellite passing through the strip; The output module is used to output the coverage area of ​​each strip in the satellite coverage area, the total coverage area of ​​all strips and the coverage ratio according to the final circle information.

9. An electronic device, characterized in that: include: one or more processors; A storage device for storing one or more programs; 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 to 7.

10. A computer readable medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the method according to any one of claims 1 to 7 is implemented.

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