CN112685685B - Analytic calculation method for discontinuous coverage of regressive orbit satellite constellation to ground - Google Patents
Analytic calculation method for discontinuous coverage of regressive orbit satellite constellation to ground Download PDFInfo
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Abstract
The application relates to an analytic calculation method for discontinuous ground coverage of a regression orbit satellite constellation. The method comprises the following steps: the method comprises the steps of obtaining a coverage area two-dimensional graph corresponding to ground points according to ground point positions and satellite ground detection half cone angle values, projecting a running track of a regression orbit satellite into the coverage area two-dimensional graph to obtain a corresponding track line, obtaining a coverage time sequence of the regression orbit satellite to the ground points according to the track line and an intersecting line segment of the coverage area in the coverage area two-dimensional graph, obtaining a weft direction coverage characteristic of the regression orbit satellite according to the coverage time sequence of the regression orbit satellite to each ground point along the same weft, and obtaining a constellation coverage characteristic of a corresponding regression orbit satellite constellation according to the coverage time sequence and the weft direction coverage characteristic of each regression orbit satellite. The method can quickly calculate the coverage condition of the regression orbit satellite constellation to the ground point and the whole world, and can count various coverage performance parameters including revisit duration and coverage duration.
Description
Technical Field
The application relates to the field of satellite constellation ground coverage calculation, in particular to an analytic calculation method for discontinuous ground coverage of a regression orbit satellite constellation.
Background
Coverage calculations are a fundamental problem in satellite constellation design and performance analysis. For the problem of discontinuous coverage analysis, the most widely used method at present is the grid point method. The basic idea of the grid point method is: a certain number of points are arranged in an area to be analyzed, and under a given time interval and time step length, the relative position relation between each ground point and all satellites in each step length is analyzed through simulation, so that the coverage characteristics of the constellation in the time interval to all ground points can be obtained. However, the grid point method is very time consuming and the accuracy of the coverage calculation depends to a large extent on the number of selected ground points, the time interval and the time step. Some research focuses on selection strategies for ground points, but it still takes a lot of time to evaluate the global coverage performance of the constellation. In addition, the existing analysis methods for discontinuous coverage have the conditions of low calculation precision, limited application range and the like.
Disclosure of Invention
Therefore, in order to solve the above technical problems, it is necessary to provide an analytic calculation method for a regression orbit satellite constellation discontinuous coverage to ground, which can quickly and accurately calculate the satellite constellation discontinuous coverage to ground.
A method for analyzing and calculating discontinuous coverage of a regression orbit satellite constellation to the ground comprises the following steps:
and obtaining a two-dimensional map of a coverage area corresponding to the ground point according to preset ground point position data and a satellite ground detection half cone angle value.
And projecting the running track of the regression orbit satellite to a two-dimensional map of a coverage area to obtain a corresponding track line.
And acquiring an intersecting line segment of the trajectory line and the coverage area in the two-dimensional graph of the coverage area, and acquiring a coverage time sequence of the regression orbit satellite to the ground point according to the intersecting line segment.
And obtaining the coverage characteristic of the regression orbit satellite in the weft direction according to the coverage time sequence of the regression orbit satellite on each ground point along the same weft.
And obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristic of each regression orbit satellite.
In one embodiment, the obtaining method of the two-dimensional map of the coverage area of the ground point includes:
and establishing a two-dimensional coordinate system by taking the ascension point and the latitude amplitude angle of the satellite in the inertial space as an X axis and a Y axis respectively.
And obtaining the mutual visible area of the corresponding ground point and the satellite in a two-dimensional coordinate system according to the preset ground point position data and the satellite ground detection half cone angle value.
In one embodiment, the projecting the operation trajectory of the return orbit satellite into the two-dimensional map of the coverage area to obtain the corresponding trajectory line includes:
and acquiring the running track of the return orbit satellite under the earth-fixed system.
And projecting the running track into a two-dimensional map of the coverage area according to the relative position relationship to obtain a track line of the regression orbit satellite in a two-dimensional coordinate system.
In one embodiment, the step of obtaining the coverage time sequence of the regression orbit satellite to the ground point according to the intersecting line segment includes:
and calculating the time interval information corresponding to the crossed line segments.
And obtaining a covering time sequence of the regression orbit satellite to the ground point according to the obtained time period information set.
In one embodiment, the method for obtaining the coverage characteristics of the regressive orbit satellite in the weft direction includes:
and acquiring the coverage repetition period of the return orbit satellite along the weft direction.
And translating the covering time sequence according to the covering repetition period to obtain the covering characteristic of the regressive orbit satellite in the weft direction.
In one embodiment, the calculation method of the constellation coverage characteristic of the regressive orbit satellite constellation includes:
and in a regression period, calculating the total coverage interval sequence of the regression orbit satellite constellation to a single ground point according to the coverage time sequence of each regression orbit satellite in the regression orbit satellite constellation.
And in a regression period, calculating the total coverage interval sequence of the regression orbit satellite constellation to the weft according to the coverage characteristics of the weft direction of each regression orbit satellite in the regression orbit satellite constellation.
In one embodiment, the method further comprises:
and obtaining the coverage performance parameters of the regression orbit satellite constellation to the weft according to the total coverage interval sequence of the regression orbit satellite constellation to the weft. An analytic computing device of regressive orbit satellite constellation to ground discontinuous coverage, comprising:
and the coverage area two-dimensional map generation module is used for acquiring a coverage area two-dimensional map corresponding to the ground points according to the preset ground point position data and the satellite ground detection half cone angle value.
And the satellite trajectory projection module is used for projecting the running trajectory of the return orbit satellite into the two-dimensional map of the coverage area to obtain a corresponding trajectory line.
And the covering time sequence calculation module is used for acquiring the intersection line segment of the trajectory line and the covering area in the two-dimensional map of the covering area and obtaining the covering time sequence of the regression orbit satellite to the ground point according to the intersection line segment.
And the latitude direction coverage characteristic analysis module is used for obtaining the latitude direction coverage characteristic of the regression orbit satellite according to the coverage time sequence of the regression orbit satellite on each ground point along the same latitude line.
And the constellation coverage characteristic analysis module is used for obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristic of each regression orbit satellite.
A computer device comprising a memory storing a computer program and a processor implementing the steps of the method of any one of the above embodiments when executing the computer program.
A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the method of any of the above embodiments.
Compared with the prior art, the analytic computing method, the analytic computing device, the computer equipment and the storage medium for the regression orbit satellite constellation to the ground discontinuous coverage, obtaining a coverage area two-dimensional graph corresponding to ground points according to preset ground point position data and a satellite ground detection half cone angle value, projecting the running track of the regression orbit satellite into the coverage area two-dimensional graph to obtain a corresponding track line, obtaining a covering time sequence of the regression orbit satellite to the ground point according to the intersection line segment of the trajectory line and the covering area in the two-dimensional graph of the covering area, according to the covering time sequence of the regression orbit satellite to each ground point along the same latitude line, the latitude line direction covering characteristic of the regression orbit satellite is obtained, and obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristic of each regression orbit satellite. The method and the device expand the application of the two-dimensional graph of the coverage area, can quickly calculate the coverage condition of the regression orbit satellite constellation to ground points, regional targets and the whole world, and count various coverage performance parameters including revisit duration and coverage duration.
Drawings
FIG. 1 is a diagram illustrating the steps of a method for analytic computation of discontinuous coverage of a constellation of regressive orbiting satellites over the ground in one embodiment;
FIG. 2 is a schematic view of the elevating point overlooked from the north pole;
FIG. 3 is a schematic diagram of satellite ground coverage;
FIG. 4 is a schematic diagram of high and low weft coverage margin;
FIG. 5 is a schematic view of a circular coverage area in a low latitude area;
FIG. 6 is a schematic diagram of four overlay scenarios;
FIG. 7 is a schematic diagram of four coverage areas;
FIG. 8 is a schematic diagram of a satellite versus a coverage area;
FIG. 9 is a schematic diagram of the relationship between the satellites and the coverage area in the Earth's fixed system;
FIG. 10 is a schematic diagram of coverage analysis of a single star with a regression parameter of 5/1 for a single target point;
FIG. 11 is a schematic diagram illustrating the calculation of the intersection point of a satellite trajectory line and a coverage area;
FIG. 12 is a schematic view of the coverage of a single star with a low weft;
FIG. 13 is a schematic diagram showing the relationship between the maximum coverage area and the coverage area of the weft;
FIG. 14 is a schematic view of a single star versus low weft yarn coverage segmentation;
FIG. 15 is a schematic view of a single-star versus normal high weft yarn coverage segmentation;
FIG. 16 is a merged view of three satellite coverage areas;
FIG. 17 is a schematic diagram showing the relative position of each satellite trajectory with respect to the intersection of the equator;
FIG. 18 is a schematic diagram of distribution of coverage areas of satellites;
FIG. 19 is a block diagram of a computer device in one embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
In one embodiment, as shown in fig. 1, there is provided a method for analytic calculation of discontinuous coverage of a regressive orbit satellite constellation to the ground, including the following steps:
and 102, obtaining a two-dimensional map of a coverage area corresponding to the ground point according to preset ground point position data and a satellite ground detection half cone angle value.
The coverage area is used for representing the mutual visibility between the satellite and the ground points under the conical view field, and the coverage area corresponding to any ground point represents: at the current moment, all possible combinations of ascension points and latitudinal amplitude angles of the ascending intersection points of the satellite with the coverage capability of the ground point. For any one ground point, its overlay pattern in the space may be convex or concave, and it is also possible to separate into two independent convex patterns.
And 104, projecting the running track of the regression orbit satellite to a two-dimensional map of a coverage area to obtain a corresponding track line.
In an inertial space, the moving track of a single satellite in a two-dimensional map of a coverage area is a straight line, and the inclination of the moving track is determined by the change of the right ascension of a rising intersection under the perturbation of the J2 long term; and the shape of the coverage area corresponding to a certain weft moves at a constant speed along with the rotation of the earth, and the moving speed is related to the rotation angular speed of the earth. Therefore, the relative position relationship between the regression orbit satellite and the coverage area two-dimensional graph can be utilized to project the satellite running track in one orbit period into a straight line, and a plurality of orbit periods correspond to a plurality of straight lines.
And 106, acquiring an intersecting line segment of the trajectory line and the coverage area in the coverage area two-dimensional graph, and acquiring a coverage time sequence of the regression orbit satellite to the ground point according to the intersecting line segment.
When the execution obtained by the projection of the running track of the satellite passes through the coverage area in the two-dimensional map of the coverage area, the intersecting line segment of the two intersecting lines represents the time interval in which the satellite can cover the ground point. Each intersecting line segment obtained by intersecting the plurality of straight lines and the coverage area represents a time interval of the ground point covered by the satellite, and the coverage time sequence of the regression orbit satellite to the ground point can be obtained according to the intersecting line segments.
And step 108, obtaining the coverage characteristics of the regression orbit satellite in the weft direction according to the coverage time sequence of the regression orbit satellite on each ground point along the same weft.
By repeating the steps 102 to 106 to calculate the covering time sequence of a plurality of ground points on the same latitude line, the covering characteristics of the regression orbit satellite along the latitude line direction can be obtained.
And step 110, obtaining the constellation coverage characteristics of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristics of each regression orbit satellite.
Similarly, according to the coverage time sequence and the latitude direction coverage characteristic of each regressive orbit satellite, the constellation coverage characteristic of the whole constellation can be obtained.
The method expands the application of the two-dimensional graph of the coverage area, converts the motion trail of the regression orbit satellite into a plurality of straight lines on the two-dimensional graph of the coverage area, obtains the coverage time sequence of the satellite to the ground point by analyzing the condition that the straight lines are intersected with the coverage area, and can obtain the constellation latitude and global coverage performance by further analyzing the condition that the coverage characteristic changes along the latitude line. The method can quickly calculate the coverage condition of the regression orbit satellite constellation to ground points, regional targets and the whole world, and can count various coverage performance parameters including revisit duration and coverage duration.
In one embodiment, an analytic calculation method for discontinuous coverage of a regression orbit satellite constellation to the ground is provided, which includes the following steps:
step 202, establishing a two-dimensional coordinate system by taking the ascension point and the latitude argument of the satellite in the inertial space as an X axis and a Y axis respectively. And obtaining the mutual visible area of the corresponding ground point and the satellite in a two-dimensional coordinate system according to the preset ground point position data and the satellite ground detection half cone angle value.
In this embodiment, in order to ensure that the coverage sequence of any one ground point can be repeated in one regression period and obtain a stable analytic solution of discontinuous coverage, a circular regression orbit is taken as an example for calculation and explanation, and the orbit radii and the inclination angles of all satellites in a constellation are the same.
The intersection period of the satellite orbit is set as
(defined as the time interval between two successive passages of the spacecraft through the intersection), and the satellite orbit angular velocity corresponding to the period of the intersection is
(ii) a Setting a cross point day as
(the intersection day is defined as the time interval between one revolution of the zero longitude line on earth relative to the elevation intersection of the satellite's orbit). The two periods have the following relationship:
wherein the content of the first and second substances,
referred to as the period of the regression,
and
is a positive integer which is relatively prime to each other,
the regression parameters are indicated.
Is provided with
Is the equatorial radius of the earth and is,
is the angular velocity of the earth and is,
is the gravitational constant. Assuming a track radius of
At an angle of inclination of
Average angular velocity of
Is provided with
. In addition, the change rates of the ascension point right ascension angle, the perigee argument and the true perigee angle are assumed to be
，
And
then, thenThe intersection day and the intersection period may be defined as:
at the same time, is arranged at
Under the influence of perturbation, the ascension of the rising point of the satellite, the amplitude angle of the near point and the change rate of the near point angle can be respectively expressed as follows:
wherein the content of the first and second substances,
parameter of
And the second latitudinal harmonic coefficient in the earth gravitational potential expansion.
Therefore, the number of days of the intersection point corresponding to the regression cycle of a certain regression circular orbit is set as
The number of orbital intersection cycles during the regression cycle for the satellite to travel is
The track inclination angle is
The radius of the track is
Then, there are:
wherein
In fact, for any track radius (or height)
And the angle of inclination
The regression parameters of the regression trajectory defined by the tilt angle can be found
Satisfy the following requirements
And radius of
Any pre-specified accuracy can be arbitrarily approached. However, arbitrary track radii and inclinations tend toResult in being larger
Values and longer regression periods.
Analyzing the intersection point condition of the infrastar point track and the latitude line of the regression orbit satellite; the analysis was developed here taking the weft coverage of the northern hemisphere as an example. Get
When is coming into contact with
In the meantime, in one orbit period, the track of the point under the satellite of a single satellite passes through the latitude line twice, and the intersection points of the track of the point under the satellite and the latitude line in the earth fixation system are marked as an ascending point and a descending point. Figure 2 shows the rising and falling points from the north pole looking down. Wherein FIG. 2a is a ascending point, indicated by the letter A; fig. 2b shows the drop point, denoted by letter D. Where the regression parameter is 5/1 and the latitude line is located in the northern hemisphere. The lifting points and the falling points are uniformly distributed around the weft, and the interval between the adjacent lifting points or the falling points
Satisfies the following conditions:
therefore, for a low latitude area, the corresponding central angles between the adjacent ascending points and the adjacent descending points on the current latitude circle are always the same. When in use
When the satellite single track is only at latitude
The sub-star point is closest to the corresponding weft. Herein, the class is notedThe points are "vertices", denoted by the letter V, it being apparent that the spacing between adjacent vertices is also
. Thus, for a circular regression trajectory, the longitude interval between adjacent tracks on the same weft remains always at
。
The coverage model of the satellite in this embodiment mainly analyzes the maximum range (corresponding to a radian) that can be reached by the coverage area of a single satellite on a given latitude line when the satellite nadir passes through the latitude line. The earth is a standard ellipsoid with the center of the earth as
The semi-major axis (equatorial radius) of
With a flat rate of
(ii) a The radius of the satellite operation circular orbit is
The half cone angle of the ground cone cover is
. Latitude of the covered latitude center
Corresponding to a center-to-earth distance of
As shown in fig. 3. The center-to-center distance of the earth when the satellite can just cover the latitude line
Can approximately representComprises the following steps:
the corresponding geocentric coverage angle can be expressed as:
taking into account the latitude to be analyzed
Corresponding to a geocentric angle of
And
correlation, can be expressed as
Function of (2)
. Consider the following two equations:
let the non-negative roots of the above two equations be
、
Corresponding angle of coverage
、
Representing the coverage angle at the low and high weft limit, respectively, then for
In the low latitude area, the up-down lines of the satellite pass through the latitude lines, and due to the rotation of the earth, the left-right coverage range of the satellite on the latitude lines has a certain difference, but the coverage ranges when the up-down lines pass through are in a symmetrical relation; for the
When the satellite approaches the top point, the satellite only covers the latitude line once, and the coverage ranges of the satellite are equal. The low and high weft limits are shown in figure 4. Considering that the satellite is in circular coverage, and when the satellite passes through the ascending point or the descending point in the low latitude condition, the analytic expressions of the left and right maximum coverage areas cannot be directly obtained through analytic calculation, which is due to the particularity of circular coverage and the influence of earth rotation. The low latitude circular overlay is shown in figure 5.
In fig. 5, the intersection point a of the track of the subsatellite point and the latitude line is the aforementioned "lifting point". When the satellite passes near the lifting point, a certain range on the latitude line is scanned, and the left end point of the scanning range is set as
The right end point is
. Set the left end point of the range
And lift point
The corresponding circle center angle distance on the weft is
Right end point
And lift point
The corresponding circle center angle distance on the weft is
Total coverage in the weft
The calculation method is given below. Maximum coverage of left end of weft lifting point
Will appear as the latitude argument of the satellite
Located in a section
A certain position in the middle, and the corresponding maximum coverage of the right end
Will go outLatitude argument of existing satellite
Located in a section
A certain position within. The expression for the left and right coverage is:
wherein the content of the first and second substances,
for the high latitude area, iteration is also needed to solve the maximum value of the coverage, and the expression is given here:
high latitude area is based on the vertex, there is
. When the above formula is solved, the latitude amplitude and angle values meeting the precision requirement can be obtained by carrying out multiple iterations in a given interval, and then the latitude amplitude and angle values are obtained
And
the value is obtained.
In this embodiment, when a coverage area of a satellite is calculated, a two-dimensional coordinate system is established with a Right Ascension Angle (RAAN) of the satellite in an inertial space as an X axis and an latitude amplitude Angle (AOL) of the satellite as a Y axis, and the obtained coverage area is a closed area in the two-dimensional space.
The overlay pattern for a ground point may be convex or concave, and may be divided into two separate convex patterns. The coverage area can be analytically calculated by a spherical triangle correlation formula, which is described in detail below. Setting the geocentric latitude of the ground point to be analyzed as
Whereas a difference in ground point geocentric longitude will only result in a translation of the graphic along the X-axis. Setting the orbit inclination angle of the circular orbit satellite as
To and from
The coverage geocentric angle corresponding to the conical view field at the latitude of the ground point is
. When generating the coverage area, four cases need to be considered according to different latitudes, as shown in fig. 6. In fig. 6, P denotes the north pole, in fig. 6, a denotes the low weft coverage area generation method, b denotes the normal high weft coverage area generation method, c denotes the coverage area generation method of the polar circle in the overlooking direction from the north pole, and d denotes the coverage area of the equatorial ringThe specific description of the inter-generation mode is as follows:
(a) and (4) low latitude. Satisfy the requirement of
At this time, the ground point can be observed by both up-and-down movement of the satellite, and the corresponding coverage area is two independent graphs.
(b) And (5) normal high weft yarns. Satisfy the requirement of
And satisfy
Time of flight
At this time, the satellite only covers the ground point once in the uplink and downlink process, and the corresponding coverage area is an independent graph.
(c) And (6) pole rings. In case of high weft, further satisfy
And is
. At this time, the coverage interval runs through the whole X axis, namely, the satellite corresponding to any ascension point right ascension can cover the ground point in a certain latitude amplitude angle interval.
(d) An equatorial ring. In the case of high weft, further satisfy
And is
. The latitudes satisfying this condition are distributed around the equator and must be covered during one orbital cycle, with the corresponding coverage interval also extending throughout the X-axis.
The coverage areas corresponding to a, b, c, and d in fig. 6 are shown as a, b, c, and d in fig. 7, respectively, and the point in the middle of the coverage area in fig. 7 represents a satellite located directly above the ground point during the uplink or downlink process.
And step 204, acquiring the running track of the return orbit satellite under the earth-fixed system. And projecting the running track to a two-dimensional map of the coverage area according to the relative position relationship to obtain a track line of the regression orbit satellite in a two-dimensional coordinate system.
And calculating the coverage condition of the single satellite to the ground based on the regression circular orbit, the satellite coverage model and the two-dimensional graph. As shown in FIG. 8, the moving track of a single satellite on the two-dimensional graph in the inertial space is a straight line which is substantially parallel to the Y axis, and the slightly inclined line is caused by the change of the right ascension of the ascending intersection under the perturbation of the long term J2, and the corresponding speed is
. The satellite moves along the Y axis in a positive direction, and the speed is the angular speed after considering the perturbation of the J2 long-term
. The shape of the corresponding coverage area on a certain latitude line moves at a constant speed along the positive direction of the X axis along the rotation of the earth, and the speed is the rotation angular speed of the earth
。
Therefore, the relative motion relationship between the satellite and the graph can be considered, the graph translation speed is transferred to the satellite, and the graph is converted into the earth fixation system, as shown in fig. 9. At this time, the coverage area is fixed, the satellite trajectory becomes a straight line inclined to the Y axis, and a plurality of orbit periods correspond to a plurality of oblique lines. The satellite traverses a segment of the coverage area, i.e., the region representing the coverage that the satellite can complete to a ground point. The meaning of the ordinate remains unchanged at this time, but the abscissa is converted to the ascending point Longitude (LAN). Furthermore, for a regressive orbit, the slope of the satellite trajectory line at this time
The regression trajectory parameters can be expressed as:
the two-dimensional map can therefore be transformed into the earth's fixation and the coverage duration defined as the portion of the satellite orbit that intersects the coverage area.
And step 206, acquiring the intersection line segment of the track line and the coverage area in the two-dimensional map of the coverage area, and calculating time period information corresponding to the intersection line segment. And obtaining a covering time sequence of the regression orbit satellite to the ground point according to the obtained time period information set.
In the following, taking low latitude as an example, the coverage of a single star to a single ground point is analyzed, and the analysis mode of high latitude is similar. The latitude and longitude of the geocentric of the ground point in the earth-fixed system are considered to be respectively
，
. RAAN and AOL of the satellite at the current moment are respectively
，
And the rest parameter symbols are the same as those in the first section. The Greenwich mean sidereal time angle corresponding to the current time is
. In the coverage graph corresponding to the ground point at the moment, the coordinates of the upper and lower overtop points are respectively recorded as
，
Then, it is obvious that:
according to
And
the coordinates of the points can determine the specific position of the coverage area in the two-dimensional map. Further determining the position of the satellite trajectory without setting the longitude of each intersection point of the satellite and the X axis as
，
. For the current time, there are:
considering the characteristics of the regression orbit, the trajectory of the satellite on the two-dimensional map is fixed, and the longitude values of the intersection points of the subsequent trajectories and the X axis are sequentially spaced
Uniformly distributed in a two-dimensional map, fig. 10 shows
，
The case (1).
To be provided with
For reference, note that the satellite passes the second
The relative time corresponding to the intersection point is
Then, then
Necessarily the satellite intersection period
Is an integer multiple of (1), where the corresponding integer is said to be
The method comprises the following steps:
wherein the content of the first and second substances,
，
and has:
wherein the content of the first and second substances,
is that make
The smallest non-negative integer that is a positive integer. The coverage area and the position of the satellite trajectory are determined and then the coverage area condition can be calculated. When the track of the satellite intersects with the coverage area, the latitude amplitude value corresponding to the boundary of the coverage area can be generated by solving the coordinates of the intersection point. As shown in fig. 11, the boundary of the coverage area is composed of a plurality of points, and when the intersection point with the upper boundary or the lower boundary is calculated, two points located at both sides of the straight line are found
、
And respectively calculating the distance between two points and the satellite trajectory straight line
、
The latitude amplitude value at the intersection point can be obtained by means of linear interpolation
The method comprises the following steps:
the coordinate values on the y-axis where the trajectory and the coverage area intersect may be expressed as:
in a complete regression cycle, the satellites share
Rails, each rail may intersect, be tangent to, or not intersect the coverage area of the ground point. The number of tracks having intersections is not set to
The set of components is
And renumbering the tracks in order of decreasing relative time to increasing relative time as
. Is provided with
In any one rail
The latitude argument corresponding to the intersection point of the figure is respectively
、
Satisfy the following requirements
，
(ii) a The moment of the trajectory at the point of intersection is
Then the footprint of the track can be expressed as
。
Therefore, the covering sequence of the satellite to the ground point can be obtained
Wherein
. Further, the maximum revisit time length of the satellite to the target can be calculated
And length of coverage
And (3) waiting for important quality parameters, wherein the specific expression is as follows:
it should be noted that the beginning and end of the coverage duration set need to be merged so that the longest revisit time is not missed. Further, other coverage characteristics may also be obtained by the sequence of coverage durations.
And step 210, acquiring a coverage repetition period of the regression orbit satellite along the weft direction, and translating the coverage time sequence according to the coverage repetition period to obtain the coverage characteristic of the regression orbit satellite in the weft direction.
Because the track of the return orbit satellite is fixed, when the coverage of the return orbit satellite on the latitude lines is analyzed, the points with different longitudes on the latitude lines can be represented only by translating the coverage area, and the coverage characteristic of the satellite on the whole latitude lines is further obtained. Coverage area graph translation
The coverage condition of the satellite to a single target is repeated after the length of the satellite is equal to or less than the preset length, so that only selection of coverage characteristics of the satellite to a single weft is needed when the coverage characteristics of the satellite to the single weft are analyzed
The long latitude segment is analyzed and is marked as a characteristic segment. As the trajectory translates, the trajectory of the satellite enters or moves out of the pattern, which may cause a large change in the revisit characteristics of the satellite to the target, and therefore, once the trajectory of the satellite enters or moves out of the pattern, separate segmentation for statistics is required.
Taking the low weft coverage analysis as an example, starting from the right side of the lifting rail tangent to the pattern, the pattern is gradually moved to the right, corresponding to possible coverage situations as shown in fig. 12, where the bold lines indicate the presence of an intersection with the pattern. In fig. 12, a, b, c, d respectively represent four coverage cases, namely: (a) the right end of the right graph of the coverage area is intersected with the track; (b) the right end of the graph on the left side of the coverage area is intersected with the track; (c) the left end of the right graph of the coverage area is separated from the track; (d) the left end of the graph on the left side of the coverage area is separated from the trace. The four cases correspond to satellite trajectories with different numbers passing through the coverage area and therefore correspond to four coverage cases. Of course, the order of the latter three cases is related to the specific latitude, and it is possible that the corresponding length in some cases is very small or even 0. In addition, when the graph moves in the range corresponding to the same coverage condition, the corresponding coverage duration and revisit duration are not fixed values, but slightly changed.
For normal high picks, it is clear that there are only two cases (a) and (d); for polar rings or equatorial rings, this is not the caseThe revisit duration and the coverage duration both change only slightly with changes in the ground point longitude. Here, the number of coverage categories for a single satellite for a single weft is noted
Then the value may be 4 or 2 or 1, which is consistent with the conclusions in the relevant literature.
The lengths corresponding to the four coverage cases on the feature segment are further analyzed below. Considering the condition that the satellite track is exactly tangent to the graph, and calculating the maximum coverage range of the left side and the right side of the latitude line based on the satellite coverage model
And
the coverage area and the maximum coverage area of the weft have a relationship as shown in fig. 13. In FIG. 13, the distance in the X-axis direction
Can be expressed as:
taking a low latitude as an example, the coverage segmentation condition of the single star to the latitude is analyzed. The segmentation of the single star to weft coverage is shown in fig. 14. The number of the satellite tracks which can be accommodated by the uplink or downlink graph at most is set as
The method comprises the following steps:
wherein floor (X) returns the largest integer not exceeding X. In FIG. 14 are
. Accommodate
After the trace is traced, the pattern has minimal remaining space along the X-axis
Can be expressed as:
in case (a), the trajectory tangential to the right side of the ascending portion is numbered 1, and the ascending portion necessarily includes
A track, the number of the rightmost track intersecting the descending part at this time
Can be expressed as:
at this time, consideration needs to be given in two cases.
Case 1:
. In which case the descending part likewise comprises
The strip track is numbered with the corresponding leftmost track
And at a distance from the leftmost side
Can be expressed as
And the number of tracks contained in the descending part is recorded as
Then there is
. Case 2:
. In which case the descending part comprises
A track of strips having
The corresponding leftmost track is numbered
Distance from the leftmost side
Can be expressed as
. Thus, for cases 2 through 4 as described above, the amount of rightward shift required for the graphic is set to
To
Then, it is obvious that:
to pair
To
And sequencing from small to large to obtain segment lengths corresponding to the four conditions and a track number set capable of covering the ground points under each condition. The total number of the sorting modes is 6, and the length of each section is respectively set as
The uplink and downlink coverage respectively comprises a number of tracks respectively
、
The start number of the down-link containing track is
. The values of the sectional parameters for single-star versus low weft coverage for different orders are shown in table 1. In which the numbers represent a small to large order, e.g. 123 represents
。
TABLE 1 Single Star vs. Low weft fill yarn overlay segmentation parameters
For normal high picks, obviously there are only cases (a) and (d), corresponding to a number of stages of 2, as shown in fig. 15. The segment lengths and the number of dots included are shown in table 2.
TABLE 2 Single-Star versus ordinary high-weft yarn coverage segmentation parameters
For polar rings or equatorial rings, there are obviously only 1 segment, the length of which is
The corresponding number of tracks is
That is, the corresponding coverage characteristics do not vary much along the latitude, and a small segment can be selected as a representative analysis.
On the basis of the analysis, for a certain weft, only the midpoint of each arc segment is selected as a representative point for analysis, and all possible covering sequence distribution and revisiting characteristics of the current weft can be obtained. For example, when analyzing the coverage of a single-star pair of low-latitude wefts, the middle points of 4 segments are selected, and the coverage time sequence of the selected points is obtained according to the method from step 202 to step 206, which can represent the basic coverage condition of the whole weft.
Step 212, in a regression cycle, calculating a total coverage interval sequence of the regression orbit satellite constellation to a single ground point according to the coverage time sequence of each regression orbit satellite in the regression orbit satellite constellation.
The coverage of a constellation to a single ground point can be analyzed by combining the coverage of each satellite in the constellation and the duration of the coverage of each satellite in the constellation in one regression cycle can be obtained. Is set as the satellite number in the constellation
Is as follows
Number of coverage areas of a satellite, wherein
. Is provided with
Is as follows
Time of coverage of a satellite, wherein
. Then, by combining
The coverage duration of the ground point can be obtained. However, since the initial time of the coverage duration is defined as the transit time of the first intersection of the orbit and the equator, the time relationship of the satellite needs to be determined. Considering the position of the satellite in the orbit, it needs to be on
An additional time interval is added to each coverage duration of a satellite, which can be expressed as:
wherein
Is as follows
Latitudinal argument of the particle.
Furthermore, it should be noted that the coverage duration needs to be limited to one regression period for each satellite. In addition, the overlap of the coverage times of the satellites should be considered and the head and tail of each coverage sequence should be combined to obtain accurate coverage or revisit time. A simple example is shown in figure 16. Sequence of total coverage intervals of constellation to a single ground point
Can be expressed as:
step 214, in a regression period, calculating a total coverage interval sequence of the regression orbit satellite constellation to the weft according to the coverage characteristics of the weft direction of each regression orbit satellite in the regression orbit satellite constellation.
Since the coverage of the weft by a single star is segmented,for example, the low latitude is 4 segments, so for a plurality of satellites, due to the change of the relative position, the coverage condition is N times of the original coverage condition, wherein N is the number of the satellites. The relative configuration of the whole constellation can be represented by RAAN and AOL, which are denoted as:
. Starting longitude of each satellite, i.e. initial position on X-axis
The method comprises the following steps:
where the superscript 1 indicates the number of the track. The positions being distributed over 360 degrees, but being displaceable by a unit length
Transferring the positions of all satellites to the same characteristic section
This segment was then analyzed as shown in fig. 17. Setting the initial position of the reference star as the reference
After the satellite is translated to the same characteristic segment, the track number is changed into
，
Then, there are:
wherein the function
Ensure that
In the interval
In (1). Each satellite corresponds to the arc segment
Length of each coverage case
The end point positions for each coverage case can be found from tables 1 and 2. Is provided with the first
First of a satellite
Corresponding coordinates of each coverage condition on the characteristic segment
Can be expressed as:
to pair
Sorting from small to large to obtain a new endpoint sequence, here denoted as
Wherein
And is and
，
. Fig. 18 shows the distribution of the coverage of each satellite in the low latitude area on the same characteristic segment. When the number of satellites is large, small sections with short lengths can be generated by combining different coverage conditions, and when the coverage characteristics corresponding to the small sections are counted, the small sections are likely to be skipped by a traditional mode of setting a plurality of target points.
And selecting the middle point of each segment as an analysis object, and obtaining the coverage sequence condition of each satellite on each segment according to the single-satellite-to-single-target coverage analysis method. The coordinate value of the midpoint of each segment is recorded as
Wherein
Then, there are:
consider that
A satellite to
And the step of judging the coverage condition of the segment is as follows:
(1) judgment of
Midpoint coordinate values of a segment
And
the relationship between the size of the first and the second,
then get
Otherwise, get
。
(2) Judgment of
Midpoint coordinate values of a segment
And
is a distance of
And through
Find the number of the interval in which it is located, here denoted as
，
。
(3) Adopting a single-star to single-target coverage analysis method, and setting the abscissa of the reference track as
The coverage condition is selected as
At a distance from the left end of the segment of
Generating a single star to single target point coverage sequence
If the coverage area is shared
Segment, then the cover sequence can be represented as:
，
。
(4) considering the time difference between all the satellites and the reference satellite, a time difference needs to be added to the coverage sequence, and the coverage sequence can be modified to be
Wherein
Can be obtained by the formula (19).
Through the steps, the statistics can be obtained
Respectively to the satellite
The covering sequence of the segments, and thus the covering condition of the whole weft thread. It should be noted that the statistical coverage sequence endpoint time needs to be constrained within a regression period, and the revisit duration cannot be obtained simply by calculating the interval of the coverage interval, or the coverage duration can be obtained by directly accumulating the coverage intervals, and the overlapping condition of the coverage sequences and the end-to-end connection condition of the coverage segments need to be considered. Thus the constellation is right
Total coverage sequence of segments
It can be expressed as:
after obtaining the total covering sequence, the corresponding revisiting sequence is formed. Further, the constellation pair latitude can be obtained
On the characteristic section of
The segment covering time length, the revisiting time length and other quality parameters. In summary, the constellation coverage of the latitude line can be obtained at most
Each coverage variable can be solved using the method described above.
And step 216, obtaining the maximum revisit time of the latitude lines according to the total coverage interval sequence of the regression orbit satellite constellation to the latitude lines.
For satellite assemblyNumber is
By the method given above, the constellation of (1) can be calculated for latitude
The covering condition of the weft. Let the maximum latitude of the satellite coverage be
Then the latitude range to be analyzed is
To
By placing a certain number of wefts in between, global coverage analysis can be performed.
The following description will take the maximum revisit time period as an example. Here, the total number of satellites is set to
Has a constellation pair latitude of
On the weft of
The maximum revisit duration of a segment is
，
Then the maximum revisit duration of the satellite to the latitude line can be expressed as
. It should be noted that the shapes of the patterns covering the regions at symmetrical positions of north and south latitude are identical,the coverage characteristics are thus piled up along the equator of the earth, the maximum length of the revisit of the world
Can be expressed as:
other global coverage performance parameters may be calculated in a similar manner.
It should be understood that, although the steps in the flowchart of fig. 1 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps in fig. 1 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
The technical effects of the present application will be described below by way of examples. In the example, a Walker constellation is used, and the configuration parameter can be defined as N/P/F, where N represents the total number of satellites, P represents the number of orbits, and F represents the phase parameter. Two configurations were considered in the analysis, namely 3/3/1 and 10/10/8. The initial parameters of the satellite orbits in the constellation are shown in table 3.
TABLE 3 Return to orbit satellite parameters
In terms of coverage parameters, the half cone angle of the satellite ground coverage opening is set to be 65 degrees. In the aspect of ground target points, 12 target points with longitude of 0 and geographical latitude of 0-55 degrees are selected at 5-degree intervals. Let UTC time for scene start be 2021 year 1 month 1 day 0 hour 0 minutes 0 seconds, and the scene interval in STK is set to two regression cycles to avoid missing any possible revisit duration. The RAAN and AOL of the reference satellite in the initial time constellation are both 0, and the coordinate system of each satellite in the STK is set as an instantaneous true equator earth-center system. The results are compared as follows:
(1) for the 3/3/1 configuration, the calculation results of the maximum revisiting time length of the STK for each target point are basically consistent, and the deviation is controlled within 1.5 seconds; for the coverage duration of each target point, the application is consistent with the STK calculation result, and the deviation is controlled within 0.003. The comparison of the two aspects is sufficient to illustrate the accuracy of the calculations of the present application.
(2) For the 10/10/8 configuration. To further illustrate the accuracy of the calculation of the present application, the maximum revisit duration corresponding to 10 satellites is less than one orbit period. For the maximum revisit duration of each ground point, the calculation result of the method is basically consistent with the calculation result of the STK, and the deviation is within 2 seconds; for the coverage duration of each ground point, the calculation results of the application and the STK are basically consistent, and the deviation is controlled within 0.012. Another notable consequence is that the deviation in coverage time is greater than in the first case (configuration 3/3/1) because there are more satellites in this case, there are more intersections of orbit and coverage area, and the coverage time is longer. Therefore, the deviation may become large due to the accumulation.
To illustrate the superiority of the method provided by the present application, the global coverage characteristics of the constellation are compared for computational performance. The constellation and coverage parameters are set according to a reference in which the global coverage maximum revisit durations of different Walker constellations are analyzed and the results of the different methods are compared. This document considers the global coverage of the same constellation and calculates the maximum revisit duration for each constellation by analyzing different latitude intervals on the earth, the specific results are shown in table 4. The first three columns of the maximum revisit duration in the table are all the data in this reference, and the last column is calculated by the method proposed in this application.
TABLE 4 comparison of Global maximum revisit duration calculation results
For the constellation of the 5/5/4 configuration in table 4, the calculation of STK is significantly less than the other three. The length of the characteristic segment needing to be analyzed in the configuration is only 360/241=1.49 degrees, and the latitude where the global maximum revisit duration is located is about 12 degrees. A characteristic segment at the latitude is selected and can be divided into 20 segments according to the description of the above embodiment, wherein the maximum revisiting time lengths of some segments are similar or identical, and finally, the maximum revisiting time length distribution condition on the whole characteristic segment can be obtained, according to the experimental result, the maximum revising time length of most positions on the latitude is about 118 minutes, but the maximum revising time length of a few positions reaches 224 minutes, so that the positions are difficult to be captured by setting ground points in the STK, and the deviation of the calculation result in the table is caused, and the deviation is also reflected in the literature. Therefore, the method and the device can find the distribution situation of all possible maximum revisiting durations on the latitude lines, and are more accurate and reliable compared with a method for selecting ground points for statistics. To verify the above, we set 100 points on the weft of the STK, which indicates that the maximum length of revisiting is about 224.15 minutes, which is consistent with the results obtained in this application. In summary, the invention can effectively find all possible coverage features, which is much superior to the existing grid point method.
In one embodiment, an apparatus for resolving discontinuous coverage of a constellation of regressive orbiting satellites over the ground comprises:
and the coverage area two-dimensional map generation module is used for acquiring a coverage area two-dimensional map corresponding to the ground points according to the preset ground point position data and the satellite ground detection half cone angle value.
And the satellite trajectory projection module is used for projecting the running trajectory of the return orbit satellite into the two-dimensional map of the coverage area to obtain a corresponding trajectory line.
And the covering time sequence calculation module is used for acquiring the intersection line segment of the trajectory line and the covering area in the two-dimensional map of the covering area and obtaining the covering time sequence of the regression orbit satellite to the ground point according to the intersection line segment.
And the latitude direction coverage characteristic analysis module is used for obtaining the latitude direction coverage characteristic of the regression orbit satellite according to the coverage time sequence of the regression orbit satellite on each ground point along the same latitude line.
And the constellation coverage characteristic analysis module is used for obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristic of each regression orbit satellite.
In one embodiment, the coverage area two-dimensional map generation module is used for establishing a two-dimensional coordinate system by taking the ascension point and the latitude argument of the satellite in the inertial space as an X axis and a Y axis respectively. And obtaining the mutual visible area of the corresponding ground point and the satellite in a two-dimensional coordinate system according to the preset ground point position data and the satellite ground detection half cone angle value.
In one embodiment, the satellite trajectory projection module is used for acquiring the operation trajectory of the return orbit satellite under the earth fixation system. And projecting the running track into a two-dimensional map of the coverage area according to the relative position relationship to obtain a track line of the regression orbit satellite in a two-dimensional coordinate system.
In one embodiment, the covering time sequence calculating module is configured to calculate time period information corresponding to the intersecting line segments. And obtaining a covering time sequence of the regression orbit satellite to the ground point according to the obtained time period information set.
In one embodiment, the latitude direction coverage characteristic analysis module is used for acquiring a coverage repetition period of the return orbit satellite along the latitude direction. And translating the covering time sequence according to the covering repetition period to obtain the covering characteristic of the regressive orbit satellite in the weft direction.
In one embodiment, the constellation coverage characteristic analysis module is configured to calculate, in a regression period, a total coverage interval sequence of a regression orbit satellite constellation to a single ground point according to a coverage time sequence of each regression orbit satellite in the regression orbit satellite constellation. And in a regression period, calculating the total coverage interval sequence of the regression orbit satellite constellation to the weft according to the coverage characteristics of the weft direction of each regression orbit satellite in the regression orbit satellite constellation.
In one embodiment, the system further comprises a maximum revisit time calculation module, configured to obtain the maximum revisit time for the latitude line according to the total coverage interval sequence of the regression orbit satellite constellation for the latitude line.
For specific limitations of the analysis and calculation device for discontinuous coverage of the regressive orbit satellite constellation to the ground, reference may be made to the above limitations of the analysis and calculation method for discontinuous coverage of the regressive orbit satellite constellation to the ground, which are not described herein again. The modules in the analytic computing device for discontinuous ground coverage of the above-mentioned regressive orbit satellite constellation can be wholly or partially realized by software, hardware and a combination thereof. The modules can be embedded in a hardware form or independent from a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.
In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as shown in fig. 19. The computer device includes a processor, a memory, a network interface, a display screen, and an input device connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program is executed by a processor to implement a method of analytical computation of the recurrent orbiting satellite constellation over discontinuous coverage of the earth. The display screen of the computer equipment can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer equipment can be a touch layer covered on the display screen, a key, a track ball or a touch pad arranged on the shell of the computer equipment, an external keyboard, a touch pad or a mouse and the like.
Those skilled in the art will appreciate that the architecture shown in fig. 19 is merely a block diagram of some of the structures associated with the disclosed aspects and is not intended to limit the computing devices to which the disclosed aspects apply, as particular computing devices may include more or less components than those shown, or may combine certain components, or have a different arrangement of components.
In one embodiment, there is provided a computer device comprising a memory storing a computer program and a processor implementing the following steps when the processor executes the computer program:
and obtaining a two-dimensional map of a coverage area corresponding to the ground point according to preset ground point position data and a satellite ground detection half cone angle value.
And projecting the running track of the regression orbit satellite to a two-dimensional map of a coverage area to obtain a corresponding track line.
And acquiring an intersecting line segment of the trajectory line and the coverage area in the two-dimensional graph of the coverage area, and acquiring a coverage time sequence of the regression orbit satellite to the ground point according to the intersecting line segment.
And obtaining the coverage characteristic of the regression orbit satellite in the weft direction according to the coverage time sequence of the regression orbit satellite on each ground point along the same weft.
And obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristic of each regression orbit satellite.
In one embodiment, a computer-readable storage medium is provided, having a computer program stored thereon, which when executed by a processor, performs the steps of:
and obtaining a two-dimensional map of a coverage area corresponding to the ground point according to preset ground point position data and a satellite ground detection half cone angle value.
And projecting the running track of the regression orbit satellite to a two-dimensional map of a coverage area to obtain a corresponding track line.
And acquiring an intersecting line segment of the trajectory line and the coverage area in the two-dimensional graph of the coverage area, and acquiring a coverage time sequence of the regression orbit satellite to the ground point according to the intersecting line segment.
And obtaining the coverage characteristic of the regression orbit satellite in the weft direction according to the coverage time sequence of the regression orbit satellite on each ground point along the same weft.
And obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the latitude direction coverage characteristic of each regression orbit satellite.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), Synchronous Link DRAM (SLDRAM), Rambus Direct RAM (RDRAM), direct bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (2)
1. An analytic calculation method for discontinuous coverage of a regressive orbit satellite constellation to the ground, the method comprising:
according to preset ground point position data and a satellite ground detection half cone angle value, obtaining a coverage area two-dimensional graph corresponding to a ground point; the method comprises the steps of acquiring a coverage area two-dimensional map of ground points, establishing a two-dimensional coordinate system by taking a rising intersection declination and a latitude argument of a satellite in an inertial space as an X axis and a Y axis respectively, and acquiring a mutual visible area of the corresponding ground point and the satellite in the two-dimensional coordinate system according to preset ground point position data and a satellite ground detection half cone angle value;
acquiring a running track of a regression orbit satellite in a geostationary system, and projecting the running track into the two-dimensional map of the coverage area according to a relative position relationship to obtain a track line of the regression orbit satellite in the two-dimensional coordinate system;
acquiring the track line and an intersecting line segment of a coverage area in the coverage area two-dimensional graph, calculating time period information corresponding to the intersecting line segment, and acquiring a coverage time sequence of the regression orbit satellite to the ground point according to an acquired set of the time period information;
obtaining the coverage characteristics of the regression orbit satellite in the weft direction according to the coverage time sequence of the regression orbit satellite on each ground point along the same weft; acquiring a coverage repetition period of the regression orbit satellite along the weft direction, and translating the coverage time sequence according to the coverage repetition period to obtain the coverage characteristic of the regression orbit satellite in the weft direction;
obtaining the constellation coverage characteristic of the corresponding constellation of the regression orbit satellite according to the coverage time sequence and the coverage characteristic of the latitude direction of each regression orbit satellite; the calculation method of the constellation coverage characteristics of the constellation of the regression orbit satellite is that in a regression period, according to the coverage time sequence of each regression orbit satellite in the constellation of the regression orbit satellite, the total coverage interval sequence of the constellation of the regression orbit satellite to a single ground point is calculated, and in a regression period, according to the coverage characteristics of the weft direction of each regression orbit satellite in the constellation of the regression orbit satellite, the total coverage interval sequence of the constellation of the regression orbit satellite to the weft is calculated.
2. The method of claim 1, further comprising:
and obtaining the coverage performance parameters of the regression orbit satellite constellation to the weft according to the total coverage interval sequence of the regression orbit satellite constellation to the weft.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110519695A (en) * | 2019-05-31 | 2019-11-29 | 中国人民解放军国防科技大学 | Database-assisted satellite system and ground cellular network spectrum sharing method |
| KR20190136851A (en) * | 2018-05-31 | 2019-12-10 | 한국전자통신연구원 | Method for estimation of snow depth from optical satellite imagery using improved Snow Cover Fraction equation and Apparatus Thereof |
| CN112118041A (en) * | 2020-09-21 | 2020-12-22 | 清华大学 | Earth station and access method and device thereof |
| CN112462401A (en) * | 2021-02-03 | 2021-03-09 | 武汉准望科技有限公司 | Urban canyon rapid detection method and device based on floating vehicle track data |
Family Cites Families (1)
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20190136851A (en) * | 2018-05-31 | 2019-12-10 | 한국전자통신연구원 | Method for estimation of snow depth from optical satellite imagery using improved Snow Cover Fraction equation and Apparatus Thereof |
| CN110519695A (en) * | 2019-05-31 | 2019-11-29 | 中国人民解放军国防科技大学 | Database-assisted satellite system and ground cellular network spectrum sharing method |
| CN112118041A (en) * | 2020-09-21 | 2020-12-22 | 清华大学 | Earth station and access method and device thereof |
| CN112462401A (en) * | 2021-02-03 | 2021-03-09 | 武汉准望科技有限公司 | Urban canyon rapid detection method and device based on floating vehicle track data |
Non-Patent Citations (2)
| Title |
|---|
| 《一种提高地基伪卫星系统接收机测距性能的反馈校正算法》;何成龙;《"2015 年全国遥感遥测遥控学术年会"论文集》;20151231;全文 * |
| 《基于几何拓扑的遥感卫星高精度对地覆盖分布式算法研究与应用》;吴晓洋;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20170331;全文 * |
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