CN112945241B - Satellite orbit evaluation method based on observation window and tracking arc segment - Google Patents
Satellite orbit evaluation method based on observation window and tracking arc segment Download PDFInfo
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Abstract
The invention discloses a satellite orbit evaluation method based on an observation window and a tracking arc segment, which comprises the following steps of evaluating a target reconnaissance window by a satellite and evaluating the tracking arc segment of the satellite by a ground receiving station; the method of the invention mainly solves the problem of the reconnaissance window evaluation of the satellite operation orbit scheme to the target area and the problem of the tracking arc section evaluation of the ground receiving station to the satellite operation orbit scheme.
Description
Technical Field
The invention belongs to the technical field of satellite orbit evaluation, and particularly relates to a satellite orbit evaluation method based on an observation window and a tracking arc segment.
Background
The satellite orbit evaluation method based on the observation window and the tracking arc section is mainly applied to the orbit planning evaluation problem of the solid rocket launching low-orbit earth observation satellite, and aims to judge whether the planned satellite orbit can support the realization of the quick and effective observation of the target area. Aiming at the detection requirements of different types of target areas, the emission windows of the target areas need to be specifically analyzed and calculated according to the constraint conditions such as emission, measurement and control, illumination and the like, and the orbit scheme design is carried out by combining a satellite emission orbit model, an orbit regression characteristic constraint, a target area illumination condition constraint and an accurate earth motion model. The conventional liquid rocket launching earth observation satellite orbit planning is different from that of a solid rocket in the task design concept, the conventional earth observation task firstly launches an earth observation satellite, and after a specific observation target is given, the satellite is sent into an observation orbit through orbital maneuver to observe the target. The incompatibility of the orbit evaluation method is determined by the difference of the design concept of the orbit scheme and the difference of the types of the carrier rockets.
Disclosure of Invention
In view of this, the invention provides a satellite orbit evaluation method based on an observation window and a tracking arc segment, which can realize orbit planning evaluation of a low-orbit earth observation satellite launched by a solid rocket.
The technical scheme for realizing the invention is as follows:
a satellite orbit assessment method based on observation windows and tracking arc segments comprises the following steps that a satellite assesses a target reconnaissance window and a ground receiving station assesses the tracking arc segments of the satellite;
the satellite evaluation of the target reconnaissance window comprises the following steps:
reading the current assessment days of a reconnaissance window and the current julian day time of the epoch time of the orbit entry point of the satellite orbit; reading six parameters of the current satellite orbit: the device comprises a semi-major axis of a track, eccentricity, a track inclination angle, a rising intersection declination, an argument of a near point and a true near point angle; reading geodetic longitude and latitude and height information of a target point position, and converting the geodetic latitude information of the target point into geocentric latitude of the target point; according to the maximum visual angle of the reconnaissance satellite, calculating geocentric latitude angle values which are corresponding to the maximum visual angle and increase detection redundancy; according to the read input parameters, calculating a perigee argument derivative, a rising point right ascension derivative, a mean anomaly angle derivative and an orbit period of the current satellite orbit, and calculating an integer second value of the satellite orbit period;
Step two: calculating the time distribution of the satellite detection cone entering the target latitude circle and leaving the target latitude circle in the 1 st orbit period after the satellite enters the orbit;
step three: processing and analyzing the time distribution of the satellite detection cone crossing the target latitude circle in the 1 st orbit period after the orbit is entered, calculating the total times of the satellite detection cone crossing the target latitude circle in the number of evaluation days of a reconnaissance window, and storing the time distribution of each time the satellite detection cone enters the target latitude circle and leaves the target latitude circle;
step four: calculating the longitude range of the satellite detection cone entering and leaving the target latitude circle in the assessment days of the reconnaissance window, and preliminarily judging whether the longitude of the target point is in the longitude range;
step five: analyzing the condition that a target point area is possibly detected when the satellite detection cone enters and leaves a target latitude circle;
step six: carrying out final validity judgment on the reconnaissance window, and finally reserving the valid reconnaissance window;
the method for evaluating the tracking arc segment of the satellite by the ground receiving station comprises the following steps:
the first step is as follows: reading the current number of evaluation days of a reconnaissance window and the current time of the julian day of the epoch moment of the orbiting point of the satellite orbit; reading six parameters of the current satellite orbit: the device comprises a semi-major axis of a track, eccentricity, a track inclination angle, a rising intersection declination, an argument of a near point and a true near point angle; reading geodetic latitude and longitude and height information of a ground receiving station, and converting the geodetic latitude information of the receiving station into a geocentric latitude of a target point; according to the minimum constraint of the pitch angle of the ground receiving station, calculating the constraint of the included angle between the satellite which increases the redundancy quantity and the geocentric of the ground station corresponding to the minimum constraint of the pitch angle, and defining the initial latitude coverage range of the ground receiving station; according to the read input parameters, calculating a perigee argument derivative, a rising point right ascension derivative, a mean anomaly angle derivative and an orbit period of the current satellite orbit, and calculating an integer second value of the satellite orbit period;
The second step: calculating the time distribution of the initial latitude coverage range of the ground receiving station when the satellite subsatellite enters and leaves within the 1 st orbit period time after the satellite enters the orbit;
the third step: processing and analyzing the time distribution of the time when the subsatellite point enters and leaves the coverage range of the primary latitude of the ground receiving station in the 1 st orbit period after the orbit is entered; calculating the total times of the satellite subsatellite points passing through the preliminary latitude coverage range of the receiving station within the assessment time of the reconnaissance window, and storing the time distribution of each time the satellite subsatellite points enter and leave the preliminary latitude coverage range of the ground receiving station;
the fourth step: calculating the longitude range of the sub-satellite point entering and leaving the primary latitude coverage range of the receiving station within the evaluation time of the reconnaissance window, and preliminarily judging whether the longitude of the ground receiving station is within the longitude range;
the fifth step: analyzing the condition that the subsatellite point possibly enters a tracking arc section of the ground receiving station when entering and leaving the primary latitude coverage range of the receiving station;
and a sixth step: and carrying out final validity judgment on the reconnaissance window, and finally reserving the valid reconnaissance window.
Further, the second step is specifically as follows:
(1) calculating the orbit of the satellite earth points by using the orbit earth longitude and latitude, the earth center longitude and latitude and a target point vector included angle calculation method of the satellite earth points, and returning the earth longitude and latitude and the earth center longitude and latitude of the satellite earth points;
(2) And (3) calculating the time distribution of the satellite detection cone transit target latitude circle according to the current time sub-satellite geocentric latitude obtained by the calculation in the step (1).
Further, the fourth step is specifically:
(1) reading initial estimation time when the satellite detection cone enters a target latitude circle and leaves the target latitude circle;
(2) and respectively calculating the longitude ranges of the satellite detection cone entering and leaving the target latitude circle by using the calculation methods of the geodetic longitude and latitude, the geocentric longitude and latitude and the vector included angle of the satellite sub-satellite track at the entering moment and the leaving moment, and if the longitude of the target point is in the longitude range, storing the transit parameters.
Further, the fifth step is specifically:
(1) reading initial estimation time when the current satellite detection cone enters a target latitude circle and leaves the target latitude circle;
(2) carrying out satellite lower point trajectory calculation at intervals of 0.1 second in a time window when the current satellite detection cone enters and leaves a target latitude circle; and whether the satellite can detect the target point is judged.
Further, the second step is specifically:
(1) calling a satellite earth longitude and latitude, geocentric longitude and latitude and vector included angle calculation method to calculate the satellite earth orbit satellite earth orbit point track, and returning the satellite earth orbit longitude and latitude and geocentric longitude and latitude of the satellite earth orbit point;
(2) And calculating the time distribution of the satellite subsatellite point entering and leaving the primary latitude coverage range of the ground receiving station according to the current subsatellite point geocentric latitude obtained by calculation.
Further, the fourth step is specifically:
and reading initial estimation time when the satellite substellar point enters and leaves the primary latitude coverage range of the receiving station, respectively calling satellite substellar point track geodetic longitude and latitude, geocentric longitude and latitude and vector included angle calculation methods for the entering time and the leaving time to calculate the longitude range of the satellite substellar point entering and leaving the primary latitude coverage range of the receiving station, and if the longitude of the ground receiving station is in the longitude range, storing the transit parameter.
Further, the fifth step is specifically:
(1) reading initial estimation time when a satellite subsatellite point enters and leaves a primary latitude coverage range of a receiving station;
(2) and (4) calculating the trajectory of the satellite lower points at intervals of 0.1 second in a time window of the initial latitude coverage range of the satellite lower point crossing, and judging whether the satellite can enter a receiving station tracking arc section.
Further, the method for calculating the geodetic longitude and latitude, the geocentric longitude and latitude and the target point vector included angle of the satellite subsatellite point track specifically comprises the following steps:
1. calculating a position vector of the satellite in the geocentric orbit coordinate system according to the semi-major axis of the satellite and the current approximate point angle;
2. Calculating the ascent point right ascent of the satellite running orbit at the current moment according to the relative orbit entering moment time difference and the ascent point right ascent derivative;
3. calculating the near-location argument of the satellite running orbit at the current moment according to the relative orbit-entering time difference and the near-location argument derivative;
4. constructing a conversion matrix from a geocentric orbit coordinate system to a geocentric inertial coordinate system;
5. performing coordinate transformation on the position vector under the geocentric orbit coordinate system to obtain a position vector under an geocentric inertial ECI coordinate system;
6. converting the ECI position vector to an ECEF position vector;
7. calculating the orbit geodetic longitude and latitude and the geocentric longitude and latitude of the satellite orbit satellite at the current moment according to the ECEF position vector;
8. calculating an included angle between a (satellite to earth center) vector and a (satellite to target point) vector according to the satellite ECEF position vector and the target point ECEF position vector;
9. and calculating the included angle between the vector (from the focal center to the receiving station) and the vector (from the satellite to the receiving station) according to the ECEF position vector of the satellite, the ECEF position vector of the receiving station and the ECEF position vector of the focal center at the near side of the receiving station on the meridian plane.
Has the advantages that:
the method for evaluating the satellite orbit based on the observation window and the tracking arc section can be suitable for planning evaluation scenes of a small-inclination circular orbit, a small-inclination regression circular orbit, a sun synchronous circular regression orbit, a large elliptical orbit and a large elliptical regression orbit which are detected aiming at different types of target areas by adopting data such as selected target area information, constraint conditions of orbit regression characteristics, constraint conditions of a reconnaissance load, launching deployment parameters (including parameters such as launching point positions, launching deployment completion moments, launching orbit data and the like) and an accurate earth motion model, and mainly solves the problem of evaluation of the reconnaissance window of a satellite operation orbit scheme to the target area and the problem of evaluation of the tracking arc section of a ground receiving station to the satellite operation orbit scheme. And comparing the evaluation result with the simulation evaluation result of the STK software, and verifying the accuracy of the track evaluation calculation.
Drawings
FIG. 1 is a flowchart of satellite-to-target scout window evaluation.
Fig. 2 is a flow chart of the tracking arc segment evaluation of the ground receiving station to the satellite.
FIG. 3 is a flowchart of calculation of geodetic longitude and latitude, geocentric longitude and latitude and vector angle of the satellite subsatellite point track.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a satellite orbit evaluation method based on an observation window and a tracking arc segment. The first part is to calculate the observation window evaluation of the satellite to the ground target in a certain evaluation period according to the current satellite orbit parameter and the ground target parameter. And the second part is to calculate the tracking arc estimation of the ground receiving station to the satellite in a certain estimation period according to the current satellite orbit parameter and the ground receiving station parameter.
The basic process for estimating the observation window of the satellite on the ground target comprises the following steps:
(1) calculate the time window tBegin, tEnd for each time the satellite probe cone enters and leaves the target latitude circle during the evaluation period. Calculating the longitude range of the satellite detection cone entering and leaving the target latitude circle, and judging whether the longitude of the target point is within the longitude range;
(2) For the case of the longitude of the target point within this longitude range, the position of the satellite in the ECEF coordinate system is precisely calculated at time intervals of 0.1 second within the corresponding time window tBegin, tEnd, and the observation angle between the (satellite-to-geocentric) vector and the (satellite-to-target) vector is calculated. And calculating an observation window of the satellite for the ground target according to the space geometric relationship between the observation included angle and the maximum visual angle of the satellite.
The basic process of the ground receiving station for estimating the tracking arc section of the satellite comprises the following steps:
(1) calculate the time window tBegin, tEnd for the satellite down-satellite point to enter and leave the ground receiver station preliminary latitude coverage during the evaluation period. Calculating the longitude range of the subsatellite point entering and leaving the primary latitude coverage range of the ground receiving station, and judging whether the longitude of the ground receiving station is in the longitude range;
(2) for the case where the longitude of the earth station is within the longitude range, the position of the satellite in the ECEF coordinate system is accurately calculated at time intervals of 0.1 second within the time window tBegin, tEnd, and the tracking angle between the (center of focus to earth station) vector and the (satellite to earth station) vector is calculated. And calculating the tracking arc section of the ground receiving station to the satellite according to the space geometric relationship between the minimum and maximum pitch angle constraint of the ground receiving station and the tracking included angle.
As shown in FIG. 1, 1. evaluation process of target reconnaissance window by satellite
Reading the current assessment days of a reconnaissance window and the current julian day time of the epoch moment of the orbiting point of the satellite orbit; (2) reading six parameters of the current satellite orbit, namely orbit semi-major axis, eccentricity, orbit inclination, ascension of ascending intersection point, perigee argument and true perigee argument; (3) reading geodetic longitude and latitude and height information of a target point position, and converting the geodetic latitude information of the target point into geocentric latitude of the target point; (4) according to the maximum visual angle of the reconnaissance satellite, calculating geocentric latitude angle values which are corresponding to the maximum visual angle and increase a certain detection redundancy; (5) and accurately calculating the perigee argument derivative, the ascension derivative of the ascending point, the mean anomaly angle derivative and the orbit period of the current satellite orbit according to the read input parameters, and calculating the integer second value of the satellite orbit period.
The second step is that: calculating the time distribution of the satellite detection cone entering the target latitude circle and leaving the target latitude circle in the 1 st orbit period after the satellite enters the orbit: (1) calculating the orbit of the satellite earth points by using the orbit earth longitude and latitude, the earth center longitude and latitude and a target point vector included angle calculation method of the satellite earth points, and returning the earth longitude and latitude and the earth center longitude and latitude of the satellite earth points; (2) and calculating the time distribution of the satellite detection cone transit target latitude circle according to the current satellite down-pointing geocentric latitude obtained by the calculation.
The third step: processing and analyzing the time distribution of the satellite detection cone crossing the target latitude circle in the 1 st orbit period after the orbit is entered, calculating the total times of the satellite detection cone crossing the target latitude circle in the number of evaluation days of a reconnaissance window, and storing the time distribution of each time the satellite detection cone enters the target latitude circle and leaves the target latitude circle; for some special satellite detection cone transit target latitude circle conditions, time distribution needs to be corrected.
The fourth step: calculating the longitude range of the satellite detection cone entering and leaving the target latitude circle in the assessment days of the reconnaissance window, and preliminarily judging whether the longitude of the target point is within the longitude range: (1) reading initial estimation time when the satellite detection cone enters a target latitude circle and leaves the target latitude circle; (2) and respectively calculating the longitude ranges of the satellite detection cone entering and leaving the target latitude circle by using the calculation methods of the geodetic longitude and latitude, the geocentric longitude and latitude and the vector included angle of the satellite sub-satellite track at the entering moment and the leaving moment, and if the longitude of the target point is in the longitude range, storing the transit parameters.
The fifth step: and accurately analyzing the condition that the target point area is possibly detected when the satellite detection cone enters and leaves the target latitude circle: (1) reading initial estimation time when the current satellite detection cone enters a target latitude circle and leaves the target latitude circle; (2) the method comprises the steps of calculating the trajectory of the satellite lower point at intervals of 0.1 second in a time window when a current satellite detection cone enters and leaves a target latitude circle, and judging whether the satellite can detect a target point, specifically, calculating the included angle between a vector (from the satellite to the geocenter) and a vector (from the satellite to the target point) at the current moment by using the calculation methods of the geodetic longitude and latitude, the geocentric longitude and latitude and the vector included angle of the satellite lower point trajectory, selecting the moment which is smaller than the maximum visual angle of the satellite for the first time as the moment of entering the current reconnaissance window, selecting the moment which is larger than the maximum visual angle of the satellite for the first time after entering the reconnaissance window as the moment of exiting the reconnaissance window, and storing the moment of entering and leaving the current reconnaissance window.
And a sixth step: and carrying out final validity judgment on the reconnaissance window, and finally reserving the valid reconnaissance window.
As shown in fig. 2, 2. evaluation of tracking arc of satellite by ground receiving station
The first step is as follows: (1) reading the number of days evaluated by a current reconnaissance window and the current orbital tracking point epoch time julian day time of a satellite orbit; (2) reading six parameters of the current satellite orbit: the device comprises a semi-major axis of a track, eccentricity, a track inclination angle, a rising intersection declination, an argument of a near point and a true near point angle; (3) reading geodetic latitude and longitude and height information of a ground receiving station, and converting the geodetic latitude information of the receiving station into a geocentric latitude of a target point;
(4) according to the minimum constraint of the pitch angle of the ground receiving station, calculating the satellite and ground station geocentric included angle constraint which is added with a certain redundancy amount and corresponds to the minimum constraint of the pitch angle, and defining the initial latitude coverage range of the ground receiving station;
(5) and accurately calculating the perigee argument derivative, the ascension derivative of the ascending point, the mean anomaly angle derivative and the orbit period of the current satellite orbit according to the read input parameters, and calculating the integer second value of the satellite orbit period.
The second step is that: calculating the time distribution of the initial latitude coverage range of the satellite subsatellite entering and leaving the ground receiving station within the 1 st orbit period time after the satellite enters the orbit: (1) calling a satellite earth longitude and latitude, geocentric longitude and latitude and vector included angle calculation method to calculate the satellite earth orbit satellite earth orbit point track, and returning the satellite earth orbit longitude and latitude and geocentric longitude and latitude of the satellite earth orbit point; (2) and calculating the time distribution of the satellite subsatellite point entering and leaving the primary latitude coverage range of the ground receiving station according to the current subsatellite point geocentric latitude obtained by the calculation.
The third step: and processing and analyzing the time distribution of the satellite points entering and leaving the primary latitude coverage range of the ground receiving station in the 1 st orbit period after the orbit is entered, calculating the total times of the satellite points crossing the primary latitude coverage range of the border receiving station in the evaluation time of the reconnaissance window, and storing the time distribution of the satellite points entering and leaving the primary latitude coverage range of the ground receiving station every time. And aiming at the condition that some special satellite subsatellite points enter and leave the primary latitude coverage range of the ground receiving station, the orbit parameters are required to be combined for correction.
The fourth step: calculating the longitude range of the satellite point entering and leaving the primary latitude coverage range of the receiving station within the evaluation time of the reconnaissance window, and primarily judging whether the longitude of the ground receiving station is within the longitude range: reading initial estimation time when the satellite sub-satellite point enters and leaves the primary latitude coverage range of the receiving station, respectively calling satellite sub-satellite point track geodetic longitude and latitude, geocentric longitude and latitude and vector included angle calculation methods for the entering time and the leaving time to calculate the longitude range of the satellite sub-satellite point entering and leaving the primary latitude coverage range of the receiving station, and if the longitude of the ground receiving station is within the longitude range, storing the transit parameter;
The fifth step: accurately analyzing the condition that the subsatellite point possibly enters a tracking arc segment of the ground receiving station when entering and leaving the primary latitude coverage range of the receiving station: (1) reading initial estimation time when a satellite subsatellite point enters and leaves a primary latitude coverage range of a receiving station; (2) and (3) calculating the trajectory of the satellite lower points at intervals of 0.1 second in a time window of the transit initial latitude coverage range of the satellite lower points, and judging whether the satellite can enter a receiving station tracking arc section: and (3) calling a satellite sub-satellite point track geodetic longitude and latitude, a geocentric longitude and latitude and a vector included angle calculation method to calculate an included angle between a current (from a focus center to a receiving station) vector and a current (from a satellite to the receiving station) vector, and judging an included angle according to a set tracking arc small angle threshold and a set large angle threshold.
And a sixth step: and carrying out final validity judgment on the reconnaissance window, and finally reserving the valid reconnaissance window.
As shown in fig. 3, the method for calculating the geodetic longitude and latitude, the geocentric longitude and latitude and the target point vector included angle of the satellite sub-satellite track specifically includes:
the first step is as follows: and calculating the position vector of the satellite in the geocentric orbit coordinate system according to the semi-major axis of the satellite and the current approximate point angle.
The second step is that: and calculating the ascent point ascent meridian of the satellite running orbit at the current moment according to the relative orbit entering moment time difference and the ascent point ascent meridian derivative.
The third step: and calculating the perigee argument of the satellite running orbit at the current moment according to the relative orbit-entering time difference and the perigee argument derivative.
The fourth step: and constructing a conversion matrix from the earth center orbit coordinate system to the earth center inertia coordinate system.
The fifth step: and (4) carrying out coordinate transformation on the position vector under the geocentric orbit coordinate system to obtain the position vector under the geocentric inertial ECI coordinate system.
And a sixth step: the ECI position vector is converted to an ECEF position vector.
The seventh step: and calculating the geodetic longitude and latitude and the geocentric longitude and latitude of the orbit satellite of the satellite at the current moment according to the ECEF position vector.
Eighth step: and calculating an included angle between the (satellite to earth center) vector and the (satellite to target point) vector according to the satellite ECEF position vector and the target point ECEF position vector.
The ninth step: and calculating the included angle between the vector (from the focal center to the receiving station) and the vector (from the satellite to the receiving station) according to the ECEF position vector of the satellite, the ECEF position vector of the receiving station and the ECEF position vector of the focal center at the near side of the receiving station on the meridian plane.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A satellite orbit assessment method based on an observation window and a tracking arc segment is characterized by comprising the following steps of satellite target reconnaissance window assessment and ground receiving station satellite tracking arc segment assessment;
the satellite evaluates the target reconnaissance window, comprising the steps of:
reading the current assessment days of a reconnaissance window and the current julian day time of the epoch time of the orbit entry point of the satellite orbit; reading six parameters of the current satellite orbit: the device comprises a semi-major axis of a track, eccentricity, a track inclination angle, a rising intersection declination, an argument of a near point and a true near point angle; reading geodetic latitude and longitude and height information of a target point position, and converting the geodetic latitude information of the target point into a geocentric latitude of the target point; according to the maximum visual angle of the reconnaissance satellite, calculating geocentric latitude angle values which are corresponding to the maximum visual angle and increase detection redundancy; according to the read input parameters, calculating a perigee argument derivative, a rising point right ascension derivative, a mean anomaly angle derivative and an orbit period of the current satellite orbit, and calculating an integer second value of the satellite orbit period;
step two: calculating the time distribution of the satellite detection cone entering the target latitude circle and leaving the target latitude circle in the 1 st orbit period after the satellite enters the orbit;
Step three: processing and analyzing the time distribution of the satellite detection cone crossing the target latitude circle in the 1 st orbit period after the orbit is entered, calculating the total times of the satellite detection cone crossing the target latitude circle in the number of evaluation days of a reconnaissance window, and storing the time distribution of each time the satellite detection cone enters the target latitude circle and leaves the target latitude circle;
step four: calculating the longitude range of the satellite detection cone entering and leaving the target latitude circle in the assessment days of the reconnaissance window, and preliminarily judging whether the longitude of the target point is in the longitude range;
step five: analyzing the condition that a target point area is possibly detected when the satellite detection cone enters and leaves a target latitude circle;
step six: carrying out final validity judgment on the reconnaissance window, and finally reserving the valid reconnaissance window;
the method for evaluating the tracking arc segment of the satellite by the ground receiving station comprises the following steps:
the first step is as follows: reading the current number of evaluation days of a reconnaissance window and the current time of the julian day of the epoch moment of the orbiting point of the satellite orbit; reading six parameters of the current satellite orbit: the device comprises a semi-major axis of a track, eccentricity, a track inclination angle, a rising intersection declination, an argument of a near point and a true near point angle; reading geodetic latitude and longitude and height information of a ground receiving station, and converting the geodetic latitude information of the receiving station into a geocentric latitude of a target point; according to the minimum constraint of the pitch angle of the ground receiving station, calculating the constraint of the included angle between the satellite which increases the redundancy quantity and the geocentric of the ground station corresponding to the minimum constraint of the pitch angle, and defining the initial latitude coverage range of the ground receiving station; according to the read input parameters, calculating a perigee argument derivative, a rising point right ascension derivative, a mean anomaly angle derivative and an orbit period of the current satellite orbit, and calculating an integer second value of the satellite orbit period;
The second step is that: calculating the time distribution of the initial latitude coverage range of the ground receiving station when the satellite subsatellite enters and leaves within the 1 st orbit period time after the satellite enters the orbit;
the third step: processing and analyzing the time distribution of the time when the subsatellite point enters and leaves the coverage range of the primary latitude of the ground receiving station in the 1 st orbit period after the orbit is entered; calculating the total times of the satellite subsatellite points passing through the preliminary latitude coverage range of the receiving station within the assessment time of the reconnaissance window, and storing the time distribution of each time the satellite subsatellite points enter and leave the preliminary latitude coverage range of the ground receiving station;
the fourth step: calculating the longitude range of the sub-satellite point entering and leaving the primary latitude coverage range of the receiving station within the evaluation time of the reconnaissance window, and preliminarily judging whether the longitude of the ground receiving station is within the longitude range;
the fifth step: analyzing the condition that the subsatellite point possibly enters a tracking arc section of the ground receiving station when entering and leaving the primary latitude coverage range of the receiving station;
and a sixth step: and carrying out final validity judgment on the reconnaissance window, and finally reserving the valid reconnaissance window.
2. The satellite orbit evaluation method based on the observation window and the tracking arc segment as claimed in claim 1, wherein the second step is specifically:
(1) Calculating the orbit of the satellite earth points by using the orbit earth longitude and latitude, the earth center longitude and latitude and a target point vector included angle calculation method of the satellite earth points, and returning the earth longitude and latitude and the earth center longitude and latitude of the satellite earth points;
(2) and (2) calculating the time distribution of the satellite detection cone transit target latitude circle according to the current time sub-satellite point geocentric latitude obtained by calculation in the step (1).
3. The satellite orbit evaluation method based on the observation window and the tracking arc segment as claimed in claim 1, wherein the fourth step is specifically:
(1) reading initial estimation moments when the satellite detection cone enters a target latitude circle and leaves the target latitude circle;
(2) and respectively calculating the longitude range of the satellite detection cone entering and leaving the target latitude circle by using the calculation methods of the geodetic longitude and latitude, the geocentric longitude and latitude and the target point vector included angle of the satellite sub-satellite track for the entering time and the leaving time, and if the longitude of the target point is within the longitude range, storing the transit parameter.
4. The method for estimating the satellite orbit based on the observation window and the tracking arc segment as claimed in claim 1, wherein the fifth step is specifically:
(1) reading initial estimation time when the current satellite detection cone enters a target latitude circle and leaves the target latitude circle;
(2) Carrying out satellite lower point trajectory calculation at intervals of 0.1 second in a time window when the current satellite detection cone enters and leaves a target latitude circle; and determines whether the satellite can detect the target point.
5. The method for estimating the satellite orbit based on the observation window and the tracking arc segment as claimed in claim 1, wherein the second step is specifically as follows:
(1) calling a satellite earth longitude and latitude, a geocentric longitude and latitude and a target point vector included angle calculation method of satellite earth track to calculate satellite earth track, and returning the earth longitude and latitude and the geocentric longitude and latitude of the satellite earth track;
(2) and calculating the time distribution of the satellite subsatellite point entering and leaving the primary latitude coverage range of the ground receiving station according to the current subsatellite point geocentric latitude obtained by the calculation.
6. The method for estimating the satellite orbit based on the observation window and the tracking arc segment as claimed in claim 1, wherein the fourth step is specifically as follows:
and reading initial estimation time when the satellite substellar point enters and leaves the primary latitude coverage range of the receiving station, respectively calling the geodetic longitude and latitude of the track of the satellite substellar point, the geocentric longitude and latitude and the target point vector included angle calculation method for the entering time and the leaving time to calculate the longitude range of the satellite substellar point entering and leaving the primary latitude coverage range of the receiving station, and if the longitude of the ground receiving station is in the longitude range, storing the transit parameter.
7. The satellite orbit evaluation method based on the observation window and the tracking arc segment as claimed in claim 1, wherein the fifth step is specifically:
(1) reading initial estimation time when the satellite subsatellite point enters and leaves the primary latitude coverage range of the receiving station;
(2) and (4) calculating the trajectory of the satellite lower points at intervals of 0.1 second in a time window of the initial latitude coverage range of the satellite lower point crossing, and judging whether the satellite can enter a receiving station tracking arc section.
8. The method for evaluating the satellite orbit based on the observation window and the tracking arc segment as claimed in any one of claims 2, 3, 5 and 6, wherein the method for calculating the geodetic longitude and latitude, the geocentric longitude and latitude and the target point vector angle of the satellite subsatellite point track specifically comprises the following steps:
1. calculating a position vector of the satellite in the geocentric orbit coordinate system according to the semi-major axis of the satellite and the current approximate point angle;
2. calculating the ascent point right ascent of the satellite running orbit at the current moment according to the relative orbit entering moment time difference and the ascent point right ascent derivative;
3. calculating the near-location argument of the satellite running orbit at the current moment according to the relative orbit-entering time difference and the near-location argument derivative;
4. constructing a transformation matrix from the geocentric orbit coordinate system to the geocentric inertial coordinate system;
5. Performing coordinate transformation on the position vector under the geocentric orbit coordinate system to obtain a position vector under an geocentric inertial ECI coordinate system;
6. converting the ECI position vector to an ECEF position vector;
7. calculating the orbit geodetic longitude and latitude and the geocentric longitude and latitude of the satellite orbit satellite at the current moment according to the ECEF position vector;
8. calculating an included angle between the satellite to earth center vector and the satellite to target point vector according to the satellite ECEF position vector and the target point ECEF position vector;
9. and calculating the included angle between the vector from the focal center to the receiving station and the vector from the satellite to the receiving station according to the ECEF position vector of the satellite, the ECEF position vector of the receiving station and the ECEF position vector of the focal center at the near side of the receiving station on the meridian plane.
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