CN116975501B - Method for optimizing satellite load to ground target coverage calculation - Google Patents
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Abstract
The application discloses a method for optimizing satellite load to ground target coverage calculation, which comprises the following steps: s1, carrying out orbit forecast calculation on a target satellite through an orbit forecast model to obtain an orbit coordinate point set; s2, according to the distance between the track coordinate point and the ground targetCritical observation elevation angle of ground targetScreening the track coordinate point set; s3, calculating the time and interval of satellite load covering ground targets according to the screened orbit coordinate point set; the application uses the distance between the coordinate point of the orbit and the ground targetCritical observation elevation angle of ground targetScreening the track coordinate point set; the orbit coordinate point set obtained by orbit prediction calculation is greatly compressed, so that the time for covering a ground target by a satellite load and the time for calculating an interval are saved, and the calculation time can be shortened to about 1/6 of the original calculation time.
Description
Technical Field
The application relates to the technical field of satellite load to ground coverage calculation, in particular to a method for optimizing satellite load to ground target coverage calculation.
Background
In recent years, the number of satellites at home and abroad is rapidly developed, and the utilization and planning of satellite resources are used as important components of space survey, operation and control, and some capacities of the satellites need to be forecasted for planning and adjusting tasks. The load on/off is specified by the acting time of the satellite load and the target of interest, and the control plan is formulated by the calculation result of the load to ground coverage in advance, so that the algorithm speed and accuracy become very important concerns when the number of satellites is large. For the middle-low orbit satellite, the satellite load occupies a small part of the orbit period before reaching the upper space of the acting target, so if the time period for which most of the satellite and the target are absolutely invisible can be removed in advance, the time consumption of calculation can be greatly reduced, and the result is not greatly influenced.
No prior art is found to be the same or similar to the present application.
Disclosure of Invention
The application aims to provide a method for optimizing satellite load coverage calculation on a ground target, which solves the problems of overlong time and interval calculation time of satellite load coverage on the ground target.
The aim of the application can be achieved by the following technical scheme: a method of optimizing satellite load to ground target coverage calculations comprising the steps of:
s1, carrying out orbit forecast calculation on a target satellite through an orbit forecast model to obtain an orbit coordinate point set;
s2, according to the distance between the track coordinate point and the ground targetCritical observation elevation angle of ground targetScreening the track coordinate point set;
and S3, calculating the time and interval of satellite load covering the ground target according to the screened orbit coordinate point set.
Further: and the track coordinate list obtained by track forecast calculation is a coordinate point set with equal step length in a designated time interval.
Further: the track forecast model adopts an SGP4 track forecast model.
Further: the distance between the orbit coordinate point and the ground targetThe acquisition formula of (1) is:
wherein,is the coordinates of the ground object,is the coordinates of the satellite instantaneous orbit coordinate point.
Further: critical observation elevation angle of the ground targetThe method of iterative calculation is adopted for acquisition, and specifically comprises the following steps:
s21, setting an initial value:
；；
s22, iterative computation;
s23, judging iteration conditions;
if it isThenEnding the iteration;
otherwiseReturning to S22, continuing to perform iterative computation until the preset iterative times, and makingThe iteration is ended.
Wherein the method comprises the steps ofAs a value of the error it is,is the half cone angle of the field of view of the satellite sensor,for the radius of the earth,is the semi-major axis of the elliptical orbit of the satellite,、is a process value.
The application has the beneficial effects that:
1. the application uses the coordinate points according to the track and the ground targetsDistance ofCritical observation elevation angle of ground targetScreening the track coordinate point set; the orbit coordinate point set obtained by orbit prediction calculation is greatly compressed, so that the time for covering a ground target by a satellite load and the time for calculating an interval are saved, and the calculation time can be shortened to about 1/6 of the original calculation time.
2. The application adopts an iterative calculation method to obtain the critical observation elevation angle of the ground targetThe sensor half cone angle and the satellite elliptical orbit value are comprehensively utilized to obtainThe method can accurately remove the set of the track coordinate points of which the satellite load and the ground target are invisible, and has higher precision and accuracy.
3. The track coordinate list obtained by track prediction calculation is a coordinate point set with equal step length in a designated time interval, the obtained track coordinate points are distributed continuously and regularly, the subsequent calculation is convenient, a track SGP4 prediction model is adopted during the track prediction calculation, the calculation efficiency of the SGP4 track prediction model is higher, and higher precision can be ensured near the root epoch time.
Drawings
FIG. 1 is a flow chart of a method for optimizing satellite load to ground target coverage calculation according to the present application.
Detailed Description
Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar symbols indicate like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present application and are not to be construed as limiting the present application.
As shown in fig. 1, the application discloses a method for optimizing satellite load to ground target coverage calculation, which comprises the following steps:
s1, carrying out orbit forecast calculation on a target satellite through an orbit forecast model to obtain an orbit coordinate point set;
s2, according to the distance between the track coordinate point and the ground targetCritical observation elevation angle of ground targetScreening the track coordinate point set;
and S3, calculating the time and interval of satellite load covering the ground target according to the screened orbit coordinate point set.
The track coordinate list obtained by track forecast calculation is a coordinate point set with equal step length in a designated time interval, the obtained track coordinate points are distributed continuously and regularly, the subsequent calculation is convenient, a track SGP4 forecast model is adopted during the track forecast calculation, the calculation efficiency of the SGP4 track forecast model is higher, and higher precision can be ensured near the root epoch time; by converting the two lines of numbers into the kepler six numbers, the near-place height of the satellite orbit ellipse can be obtained, whether the acting distance of the satellite load is smaller than the near-place height is judged, and if the acting distance of the satellite load is smaller than the near-place height, the satellite load coverage period can be preliminarily judged not to exist in the whole period.
When the acting distance of the satellite load is greater than the height of the near-ground point, calculating the distance between each orbit coordinate point and the ground target，
Distance between track coordinate point and ground targetThe acquisition formula of (1) is:
wherein,is the coordinates of the ground object,the coordinate system adopted is the space rectangular coordinate under the ground fixed system.
By satellite range and distanceAnd (3) the orbit coordinate points which do not meet the satellite action distance can be removed, so that the preliminary screening of the orbit coordinate point set is realized.
Then further calculate the lowest observation elevation angle of the ground targetHalf cone angle through satellite load sensorAnd the semi-major axis of the elliptical orbit of the satelliteCan calculate a critical valueThe critical observation elevation angle of the ground target can be obtained by adopting an iterative calculation method：
First, an initial value is set:
；；
wherein the method comprises the steps ofAs a value of the error it is,is the half cone angle of the field of view of the satellite sensor,for the radius of the earth,is the half-length axis distance of the satellite's elliptical orbit,is a process value.
Then obtaining the condition value of iterative decisionAnd carrying out iterative calculation according to the conditions:
finally, according to the iteration condition, ifThenObtaining the finalValue, ending iteration;
if it does not meetConditions of (1)Then, continuing the iterative computation, if the iteration number exceeds a preset iteration number, for example, the iteration number exceeds 100 times, and the iteration computation stopping condition still cannot be met, makingThe iteration is ended.
After obtainingAfter the value, according toValue traversal is based on distanceThe track coordinate point set of preliminary screening can realize further screening to the track coordinate point set, eliminates the track coordinate point that does not satisfy the requirement to great reduction track coordinate point set's scope.
According to the screened orbit coordinate point set, the time and interval of satellite load covering ground targets are calculated, so that the calculation time can be greatly saved, and the calculation time can be shortened to about 1/6 of the original calculation time (the precision loss is within 10 ms).
The foregoing is only a preferred embodiment of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art, who is within the scope of the present application, should make equivalent substitutions or modifications according to the technical scheme of the present application and the inventive concept thereof, and should be covered by the scope of the present application.
Claims (4)
1. A method for optimizing satellite load to ground target coverage calculation, characterized by: the method comprises the following steps:
s1, carrying out orbit forecast calculation on a target satellite through an orbit forecast model to obtain an orbit coordinate point set;
s2, according to the distance between the track coordinate point and the ground targetAnd critical observation elevation angle of ground target +.>Screening the track coordinate point set;
s3, calculating the time and interval of satellite load covering ground targets according to the screened orbit coordinate point set;
critical observation elevation angle of the ground targetThe method of iterative calculation is adopted for acquisition, and specifically comprises the following steps:
s21, setting an initial value:
；/>；/>；
s22, iterative computation;
；
；
s23, judging iteration conditions;
if it isThen->Ending the iteration;
otherwiseReturning to S22, continuing to perform iterative computation until the preset iterative times are reached, and enabling +.>Ending the iteration;
wherein the method comprises the steps ofFor error value +.>For the half cone angle of the satellite sensor field of view, < >>For the earth radius>Is the semi-major axis of the satellite elliptical orbit, +.>、/>Is a process value.
2. A method of optimizing satellite load to ground target coverage calculations as recited in claim 1, wherein: and the track coordinate list obtained by track forecast calculation is a coordinate point set with equal step length in a designated time interval.
3. A method of optimizing satellite load to ground target coverage calculations as recited in claim 1, wherein: the track forecast model adopts an SGP4 track forecast model.
4. A method of optimizing satellite load to ground target coverage calculations as recited in claim 1, wherein: the distance between the orbit coordinate point and the ground targetSeparation ofThe acquisition formula of (1) is:
；
wherein,for the coordinates of ground targets>Is the coordinates of the satellite instantaneous orbit coordinate point.
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