CN115032671A - Low-earth-orbit satellite tracking and forecasting time period calculation method and device - Google Patents
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Abstract
The embodiment of the application discloses a method and a device for calculating a low-earth-orbit satellite tracking forecast time period, wherein the method comprises the following steps: calculating satellite ephemeris data in a given time period according to the satellite orbit number; screening out possible visual time periods of the observation station and the satellite from the given time period according to the satellite orbit number and the satellite ephemeris data; and traversing and calculating satellite ephemeris data corresponding to the possible visual time period to acquire satellite tracking forecast time period information. Through the scheme of the embodiment, the calculation efficiency is improved.
Description
Technical Field
The embodiment of the application relates to the aerospace technology, in particular to a method and a device for calculating a low-orbit satellite tracking forecast time period.
Background
Calculation of the low-earth-orbit satellite tracking and forecasting time period is an important link of a satellite measurement, operation and control system, and provides accurate time guiding information for satellite measurement and control instruction uploading, remote sensing data downlink and the like. According to the conventional satellite tracking forecasting time period calculation method, the information of the position, the pitch and the like of each point of the satellite ephemeris under a survey station coordinate system is calculated in a traversing manner according to the information of the satellite ephemeris, the survey station position and the like, and a time period range which accords with certain pitch angle information is given, namely the satellite tracking forecasting time period. The method mainly comprises the following steps: (1) calculating satellite ephemeris data according to the satellite orbit parameters; (2) according to the position information of the survey station and the satellite ephemeris data, the azimuth angle and the pitch angle of the satellite under the coordinate system of the survey station are calculated in a traversing manner; (3) and giving a time period (namely a satellite tracking forecast time period) according with the tracking pitch angle according to the satellite tracking pitch angle constraint condition.
The conventional satellite tracking forecast time period calculation method needs to traverse each point of the satellite ephemeris, so that the calculation amount is large and the calculation time is long.
Disclosure of Invention
The embodiment of the application provides a method and a device for calculating a low-earth-orbit satellite tracking forecast time period, which can improve the calculation efficiency.
The embodiment of the application provides a method for calculating a low-earth-orbit satellite tracking forecast time period, which comprises the following steps:
calculating satellite ephemeris data in a given time period according to the satellite orbit number;
screening out possible visual time periods of the observation station and the satellite from the given time period according to the satellite orbit number and the satellite ephemeris data;
and traversing and calculating the satellite ephemeris data of the possible visual time period to acquire satellite tracking forecast time period information.
In an exemplary embodiment of the present application, the screening out a possible visible time period between the survey station and the satellite from the given time period according to the number of satellite orbits and the satellite ephemeris data may include:
calculating the included angle between the orbit surfaces of the survey station and the satellite according to the satellite ephemeris data
；
Calculating the critical geocentric included angle between the satellite orbit plane and the survey station when the satellite and the survey station are visible according to the satellite orbit number
；
According to the critical geocentric angle
And the included angle of the track surface
A possible visual time period is screened out from the given time period.
In an exemplary embodiment of the application, the included angle between the orbit plane of the survey station and the satellite is calculated according to the satellite ephemeris data
The method comprises the following steps:
calculating the normal direction of the orbital plane of the earth-fixed coordinate system according to the satellite ephemeris data
Coordinate vector of survey station of geostationary coordinate system
；
According to the normal direction of the track surface of the ground-fixed coordinate system
And the coordinate vector of the measuring station of the earth-fixed coordinate system
Calculating the included angle of the track surface
。
In an exemplary embodiment of the present application, the satellite ephemeris data may include: position vector of earth-fixed coordinate system of satellite
Speed vector of earth-solid coordinate system
And a spherical coordinate position component of the satellite;
according to the normal direction of the track surface of the ground-fixed coordinate system
And the coordinate vector of the measuring station of the earth-fixed coordinate system
Calculating the included angle of the track surface
The method comprises the following steps:
according to the position vector of the ground-fixed coordinate system
The speed vector of the ground-solid coordinate system
And calculating the normal direction of the track surface of the earth-fixed coordinate system by a preset first calculation formula
；
Calculating the coordinate vector of the measuring station of the earth-fixed coordinate system according to the spherical coordinate position component of the satellite and a preset second calculation formula
；
According to the normal direction of the track surface of the ground-fixed coordinate system
The coordinate vector of the measuring station of the earth-fixed coordinate system
And calculating the included angle of the track surface by a preset third calculation formula
。
In an exemplary embodiment of the present application, the first calculation formula may include:
wherein:
is normal to the track surface of the ground-fixed coordinate system;
is the position vector of the earth-fixed coordinate system;
the speed vector of the ground-fixed coordinate system is obtained;
the second calculation formula includes:
wherein, the first and the second end of the pipe are connected with each other,
；
the third calculation formula may include:
。
in an exemplary embodiment of the present application, the number of satellite orbits may include: track eccentricity and track semi-major axis;
and calculating the critical geocentric included angle between the survey station and the satellite orbit surface when the satellite and the survey station are visible according to the satellite orbit number
The method comprises the following steps:
calculating the critical geocentric included angle according to the orbit eccentricity, the orbit semimajor axis, the corresponding earth radius at the position of the survey station and a preset fourth calculation formula
。
In an exemplary embodiment of the present application, the fourth calculation formula may include:
wherein a is the orbit semi-major axis, e is the orbit eccentricity, and R is the corresponding earth radius at the survey station position.
In an exemplary embodiment of the present application, the critical geocentric angle is defined according to
And the included angle of the track surface
Screening out possible visual time periods from the given time period may include:
satisfying the given time period
Satellite ephemeris data is removed;
will satisfy the given period of time
As the possible visibility period, is the period corresponding to the satellite ephemeris data.
In an exemplary embodiment of the present application, the performing a traversal calculation on the satellite ephemeris data of the possible visible time period to obtain the satellite tracking forecast time period information may include:
converting the position vector under the satellite earth-fixed coordinate system in the satellite ephemeris data of the possible visual time period into a position vector under a coordinate system of a measuring station;
calculating angle information of the satellite in the coordinate system of the measuring station according to the position vector of the satellite in the coordinate system of the measuring station;
and determining a visible time period set visible to the satellite by the survey station according to the angle information, and taking the visible time period set as a satellite tracking and forecasting time period.
In an exemplary embodiment of the present application, the angle information may include: an elevation angle;
the determining of the visible time period set of the survey station visible to the satellite according to the angle information comprises:
and taking the set of all time periods with the altitude angle larger than zero as the set of visible time periods of the survey station visible to the satellite.
The embodiment of the present application further provides a low-earth-orbit satellite tracking forecast time period calculation device, which may include a processor and a computer-readable storage medium, where instructions are stored in the computer-readable storage medium, and when the instructions are executed by the processor, the low-earth-orbit satellite tracking forecast time period calculation method is implemented.
Compared with the related art, the embodiment of the application can comprise the following steps: calculating satellite ephemeris data in a given time period according to the satellite orbit number; screening out possible visual time periods of the observation station and the satellite from the given time period according to the satellite orbit number and the satellite ephemeris data; and traversing and calculating satellite ephemeris data corresponding to the possible visual time period to acquire satellite tracking forecast time period information. Through the scheme of the embodiment, the calculation efficiency is improved.
The beneficial effect of this application does: the remote sensing satellite carries out satellite tracking in a low-orbit satellite orbit, and a method with higher calculation efficiency is provided for calculating the satellite tracking forecast time period; according to the characteristics of the low-orbit remote sensing satellite orbit, the satellite enters and exits the ground station (or called a survey station) in two time periods, and the ground station cannot track the satellite outside the two time periods, so that the time period screening step is added, 80% of the time periods which cannot be tracked are screened out, the traversal calculation time is reduced to about 20% of the original traversal calculation time, the calculation amount of the screening is small, and the efficiency is further improved.
Additional features and advantages of the present application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the present application. Other advantages of the present application may be realized and attained by the instrumentalities and combinations particularly pointed out in the specification and the drawings.
Drawings
The accompanying drawings are included to provide an understanding of the present disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the examples serve to explain the principles of the disclosure and not to limit the disclosure.
Fig. 1 is a flowchart of a method for calculating a low-earth-orbit satellite tracking forecast time period according to an embodiment of the present application;
FIG. 2 is a diagram illustrating an exemplary embodiment of the present disclosure for calculating a track plane included angle according to a normal direction of a track plane of a geostationary coordinate system and coordinate vectors of a survey station of the geostationary coordinate system
A method flowchart of (2);
FIG. 3 is a schematic diagram of the relative positions of the survey station and the satellites according to the embodiment of the application;
FIG. 4 is a flowchart of a method for obtaining satellite tracking forecast time period information by performing traversal calculation on satellite ephemeris data of a possible visible time period according to an embodiment of the present disclosure;
fig. 5 is a block diagram of a low earth orbit satellite tracking forecast time period calculation device according to an embodiment of the present application.
Detailed Description
The description herein describes embodiments, but is intended to be exemplary, rather than limiting and it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible that are within the scope of the embodiments described herein. Although many possible combinations of features are shown in the drawings and discussed in the detailed description, many other combinations of the disclosed features are possible. Any feature or element of any embodiment may be used in combination with or instead of any other feature or element in any other embodiment, unless expressly limited otherwise.
The present application includes and contemplates combinations of features and elements known to those of ordinary skill in the art. The embodiments, features and elements disclosed in this application may also be combined with any conventional features or elements to form a unique inventive concept as defined by the claims. Any feature or element of any embodiment may also be combined with features or elements from other inventive aspects to form yet another unique inventive aspect, as defined by the claims. Thus, it should be understood that any of the features shown and/or discussed in this application may be implemented alone or in any suitable combination. Accordingly, the embodiments are not limited except as by the appended claims and their equivalents. Further, various modifications and changes may be made within the scope of the appended claims.
Further, in describing representative embodiments, the specification may have presented the method and/or process as a particular sequence of steps. However, to the extent that the method or process does not rely on the particular order of steps set forth herein, the method or process should not be limited to the particular sequence of steps described. Other orders of steps are possible as will be understood by those of ordinary skill in the art. Therefore, the particular order of the steps set forth in the specification should not be construed as limitations on the claims. Further, the claims directed to the method and/or process should not be limited to the performance of their steps in the order written, and one skilled in the art can readily appreciate that the sequences may be varied and still remain within the spirit and scope of the embodiments of the present application.
The embodiment of the application provides a method for calculating a low-earth-orbit satellite tracking forecast time period, as shown in fig. 1, the method may include steps S101 to S103:
s101, satellite ephemeris data in a given time period are calculated according to the satellite orbit number;
s102, screening out possible visual time periods of the survey station and the satellite from the given time period according to the satellite orbit number and the satellite ephemeris data;
s103, performing traversal calculation on the satellite ephemeris data of the possible visual time period to acquire satellite tracking forecast time period information.
In the exemplary embodiment of the application, it is known that the current remote sensing satellite adopts a low-orbit satellite orbit, and a method with higher efficiency is provided for calculating the satellite tracking forecast time period aiming at the tracking current situation of the current remote sensing satellite. Specifically, calculation can be performed according to the orbit characteristics of the low-orbit remote sensing satellite: the method comprises the steps that a satellite enters and exits a ground station (or called an observation station) in two time periods (namely visible time periods), and the ground station cannot track the satellite outside the two time periods.
In an exemplary embodiment of the present application, the calculation method for calculating satellite ephemeris data in a given time period (the given time period may be a period including a required satellite forecast time period, for example, 24 hours in the future) according to the satellite orbit root number may include a numerical method and an analysis method, wherein input parameters are kepler (kepler) orbit root data, and output parameters are position and velocity of the satellite in an inertial coordinate system (J2000) and a ground-fixed coordinate system (WGS 84); the geostationary position vector and the geostationary velocity vector referred to hereinafter are the outputs herein, and are the position and velocity of the satellite in the inertial frame (J2000) and the geostationary frame (WGS 84). In general, the numerical method can consider more complex perturbation conditions, the calculation precision is higher, and the calculation speed of the analytical method is higher; both numerical and analytical methods currently have standard calculation procedures and methods, which are not described in detail herein.
In an exemplary embodiment of the present application, the screening out a possible visible time period between the survey station and the satellite from the given time period according to the number of satellite orbits and the satellite ephemeris data may include:
calculating the orbital plane included angle between the survey station and the satellite according to the satellite ephemeris data
；
Calculating the critical geocentric included angle between the satellite orbit plane and the survey station when the satellite and the survey station are visible according to the satellite orbit number
；
According to the critical geocentric angle
And the included angle of the track surface
A possible visual time period is screened out from the given time period.
In an exemplary embodiment of the application, the included angle between the orbit plane of the survey station and the satellite is calculated according to the satellite ephemeris data
The method comprises the following steps:
calculating a normal direction of a track plane of a ground-fixed coordinate system and a coordinate vector of a measuring station of the ground-fixed coordinate system according to the satellite ephemeris data;
calculating the included angle of the track surface according to the normal direction of the track surface of the earth-fixed coordinate system and the coordinate vector of the measuring station of the earth-fixed coordinate system
。
In an exemplary embodiment of the present application, the satellite ephemeris data may include: a position vector of a terrestrial coordinate system of the satellite, a velocity vector of the terrestrial coordinate system, and a spherical coordinate position component of the satellite.
In an exemplary embodiment of the present application, as shown in fig. 2, the track plane included angle is calculated according to the normal direction of the track plane of the geostationary coordinate system and the coordinate vector of the coordinate system of the geostationary coordinate system
May include steps S201-S203:
s201, according to the position vector of the ground-fixed coordinate system
The speed vector of the ground-solid coordinate system
And calculating the normal direction of the orbital plane of the earth-fixed coordinate system by a preset first calculation formula
。
In an exemplary embodiment of the present application, the first calculation formula may include:
wherein:
is the normal direction of the track surface of the earth-fixed coordinate system;
the position vector of the ground-fixed coordinate system is obtained;
is the speed vector of the earth-fixed coordinate system.
In an exemplary embodiment of the present application, the number of satellite orbits may include: track eccentricity and track semi-major axis; the satellite ephemeris data may include: the distance of the satellite to the earth's center.
In an exemplary embodiment of the present application, the normal direction of the orbital plane of the earth-fixed coordinate system is calculated
Previously, the distance r from the satellite to the geocentric in the given time period can be calculated according to the orbit eccentricity, the orbit semi-major axis and a preset fifth calculation formula. As shown in FIG. 3, O is the geocentric, S is the satellite position, R is the geodetic position earth radius, R is the satellite-to-geocentric distance,
is the critical geocentric angle.
In an exemplary embodiment of the present application, the fifth calculation formula may include:
；
a is the track semimajor axis, e is the track eccentricity. r is a scalar, is a vector
A (1+ e) is derived from the modulus.
S202, calculating coordinate vectors of the measuring stations of the earth-fixed coordinate system according to the spherical coordinate position component of the satellite and a preset second calculation formula
。
In an exemplary embodiment of the present application, the second calculation formula may include:
wherein, the first and the second end of the pipe are connected with each other,
In an exemplary embodiment of the present application, the second calculation formula is a coordinate vector of the measuring station in the earth-fixed coordinate system
Three rectangular coordinate components of
、
、
Component of spherical coordinates
The relationship between them.
S203, according to the normal direction of the track surface of the ground-fixed coordinate system
The coordinate vector of the measuring station of the earth fixation coordinate system
And calculating the included angle of the track surface by a preset third calculation formula 
。
In an exemplary embodiment of the present application, the third calculation formula may include:
。
in an exemplary embodiment of the present application, the number of satellite orbits may include: track eccentricity and track semi-major axis;
and calculating the critical geocentric included angle between the survey station and the satellite orbit surface when the satellite and the survey station are visible according to the satellite orbit number
The method comprises the following steps:
calculating the critical geocentric included angle according to the orbit eccentricity, the orbit semimajor axis, the corresponding earth radius at the position of the survey station and a preset fourth calculation formula
。
In an exemplary embodiment of the present application, the fourth calculation formula may include:
wherein a is the orbit semi-major axis, e is the orbit eccentricity, and R is the corresponding earth radius at the survey station position.
In an exemplary embodiment of the present application, the critical geocentric angle is defined according to
And the included angle of the track surface
Screening out possible visual time periods from the given time period, andthe method comprises the following steps:
satisfying the given time period
Satellite ephemeris data is removed;
satisfying the given time period
As the possible visibility period, is the period corresponding to the satellite ephemeris data.
In the exemplary embodiments of the present application, when
Corresponding satellite ephemeris data can be removed and reserved to meet the requirement
Satellite ephemeris data.
In an exemplary embodiment of the present application, as shown in fig. 4, the performing a traversal calculation on the satellite ephemeris data of the possible visible time period to obtain the satellite tracking forecast time period information may include steps S301 to S303:
and S301, converting the position vector in the satellite earth fixed coordinate system in the satellite ephemeris data of the possible visual time period into the position vector in the coordinate system of the observation station.
In an exemplary embodiment of the present application, the remaining satellite ephemeris data is satellite ephemeris data for a period of possible visibility. For the satellite ephemeris data, the position vector of the geodetic station geodetic coordinate system can be calculated by utilizing the conversion of the position of the geodetic coordinate system (wgs84) and the height of longitude and latitude according to the longitude and latitude information of the geodetic station under the geodetic coordinate system
Then converting the position vector of the satellite earth-fixed coordinate system into the position vector in the coordinate system of the measuring station
：
Wherein:
，
for the station's latitude and longitude,
is referred to as rotating about the y-axis
The matrix of (a) is,
is referred to as rotating around the Z axis
The matrix of (a) is,
is the position vector of the satellite in the earth-fixed coordinate system.
S302, calculating angle information of the satellite in the coordinate system of the measuring station according to the position vector of the satellite in the coordinate system of the measuring station.
In an exemplary embodiment of the present application, the position vector of the satellite in the coordinate system of the survey station can be used as a basis
Information, calculating the altitude angle of the communication satellite relative to the survey station:
。
and S303, determining a visible time period set visible to the satellite by the survey station according to the angle information, and taking the visible time period set as a satellite tracking and forecasting time period.
In an exemplary embodiment of the present application, the angle information may include: an elevation angle;
the determining a visible time period set of the survey station visible to the satellite according to the angle information comprises:
and taking the set of all time periods with the altitude angle larger than zero as the set of visible time periods of the survey station visible to the satellite.
In the exemplary embodiments of the present application, when
The time measuring station is visible to the satellite, so the set of visible time periods is the tracking time period information.
In the exemplary embodiment of the application, by adding simple time screening calculation, most of time periods which do not need to be calculated are removed, and the overall efficiency of tracking and forecasting calculation is improved.
The embodiment of the present application further provides a low-earth-orbit satellite tracking forecast time period calculation apparatus 1, as shown in fig. 5, which may include a processor 11 and a computer-readable storage medium 12, where the computer-readable storage medium 12 stores instructions, and when the instructions are executed by the processor 11, the low-earth-orbit satellite tracking forecast time period calculation method is implemented.
In an exemplary embodiment of the present application, any of the foregoing embodiments of the method for calculating a low-earth orbit satellite tracking forecast time period may be applied to the embodiment of the apparatus, and details thereof are not repeated herein.
It will be understood by those of ordinary skill in the art that all or some of the steps of the methods, systems, functional modules/units in the devices disclosed above may be implemented as software, firmware, hardware, and suitable combinations thereof. In a hardware implementation, the division between functional modules/units mentioned in the above description does not necessarily correspond to the division of physical components; for example, one physical component may have multiple functions, or one function or step may be performed by several physical components in cooperation. Some or all of the components may be implemented as software executed by a processor, such as a digital signal processor or microprocessor, or as hardware, or as an integrated circuit, such as an application specific integrated circuit. Such software may be distributed on computer readable media, which may include computer storage media (or non-transitory media) and communication media (or transitory media). The term computer storage media includes volatile and nonvolatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules or other data, as is well known to those skilled in the art. Computer storage media includes, but is not limited to, RAM, ROM, EEPROM, flash memory or other memory technology, CD-ROM, Digital Versatile Disks (DVD) or other optical disk storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other medium which can be used to store the desired information and which can accessed by a computer. In addition, communication media typically embodies computer readable instructions, data structures, program modules or other data in a modulated data signal such as a carrier wave or other transport mechanism and includes any information delivery media as known to those skilled in the art.
Claims (10)
1. A method for calculating a low-earth-orbit satellite tracking forecast time period is characterized by comprising the following steps:
calculating satellite ephemeris data in a given time period according to the satellite orbit number;
screening out possible visual time periods of the observation station and the satellite from the given time period according to the satellite orbit number and the satellite ephemeris data;
and traversing and calculating the satellite ephemeris data of the possible visual time period to acquire satellite tracking forecast time period information.
2. The method for calculating the low-earth-orbit satellite tracking forecast time period according to claim 1, wherein the step of screening out the possible visible time periods of the survey station and the satellite from the given time period according to the satellite orbit number and the satellite ephemeris data comprises the following steps:
calculating the included angle between the orbit surfaces of the survey station and the satellite according to the satellite ephemeris data
；
Calculating the critical geocentric included angle between the satellite orbit plane and the survey station when the satellite and the survey station are visible according to the satellite orbit number
；
According to the critical geocentric angle
And the included angle of the track surface
A possible visual time period is screened out from the given time period.
3. The method according to claim 2, wherein the calculation of the orbital plane angle between the survey station and the satellite is performed according to the ephemeris data of the satellite
The method comprises the following steps:
calculating the normal direction of the orbital plane of the earth-fixed coordinate system according to the satellite ephemeris data
Coordinate vector of survey station of geostationary coordinate system
；
According to the normal direction of the track plane of the geostationary coordinate system
And the coordinate vector of the measuring station of the earth-fixed coordinate system
Calculating the included angle of the track surface
。
4. The method of calculating a low-earth-orbit satellite tracking forecast time period of claim 3, wherein the satellite ephemeris data comprises: position vector of earth-fixed coordinate system of satellite
Speed vector of earth-solid coordinate system
And a spherical coordinate position component of the satellite;
according to the normal direction of the track surface of the ground-fixed coordinate system
And the coordinate vector of the measuring station of the earth-fixed coordinate system
Calculating the included angle of the track surface
The method comprises the following steps:
according to the position vector of the ground-fixed coordinate system
The speed vector of the ground-solid coordinate system
And calculating the normal direction of the track surface of the earth-fixed coordinate system by a preset first calculation formula
；
Calculating the coordinate vector of the measuring station of the earth-fixed coordinate system according to the spherical coordinate position component of the satellite and a preset second calculation formula
；
According to the normal direction of the track plane of the geostationary coordinate system
The coordinate vector of the measuring station of the earth-fixed coordinate system
And calculating the included angle of the track surface by a preset third calculation formula
。
5. The method according to claim 4, wherein the first calculation formula includes:
wherein:
is normal to the track surface of the ground-fixed coordinate system;
the position vector of the ground-fixed coordinate system is obtained;
the speed vector of the ground-fixed coordinate system is obtained;
the second calculation formula includes:
wherein the content of the first and second substances,
the third calculation includes:
。
6. the method according to claim 1, wherein the number of the satellite orbits comprises: track eccentricity and track semi-major axis;
and calculating the critical geocentric included angle between the survey station and the satellite orbit surface when the satellite and the survey station are visible according to the satellite orbit number
The method comprises the following steps:
calculating the critical geocentric included angle according to the orbit eccentricity, the orbit semimajor axis, the corresponding earth radius at the position of the survey station and a preset fourth calculation formula
；
The fourth calculation formula includes:
wherein a is the orbit semi-major axis, e is the orbit eccentricity, and R is the corresponding earth radius at the survey station position.
7. The method as claimed in claim 2, wherein the method comprises calculating the predicted time period according to the critical geocentric angle
And the included angle of the track surface
Screening out possible visual time periods from the given time period, including:
satisfying the given time period
Satellite ephemeris data is removed;
satisfying the given time period
As the possible visibility period, is the period corresponding to the satellite ephemeris data.
8. The method as claimed in claim 1, wherein the step of performing a traversal calculation on the satellite ephemeris data of the possible visible time periods to obtain satellite tracking forecast time period information comprises:
converting the position vector under the satellite earth-fixed coordinate system in the satellite ephemeris data of the possible visual time period into a position vector under a coordinate system of a measuring station;
calculating angle information of the satellite in the coordinate system of the measuring station according to the position vector of the satellite in the coordinate system of the measuring station;
and determining a visible time period set visible to the satellite by the survey station according to the angle information, and taking the visible time period set as a satellite tracking and forecasting time period.
9. The method according to claim 8, wherein the angle information includes: an elevation angle;
the determining a visible time period set of the survey station visible to the satellite according to the angle information comprises:
and taking the set of all time periods with the altitude angle larger than zero as the set of visible time periods of the survey station visible to the satellite.
10. An apparatus for calculating a low-earth-orbit satellite tracking forecast time period, comprising a processor and a computer-readable storage medium, wherein instructions are stored in the computer-readable storage medium, and when the instructions are executed by the processor, the method for calculating a low-earth-orbit satellite tracking forecast time period is implemented according to any one of claims 1-9.
Priority Applications (1)
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| CN116609813A (en) * | 2023-05-17 | 2023-08-18 | 北京星网宇达科技股份有限公司 | Satellite orbit position determining system, method, equipment and storage medium |
| CN116996115A (en) * | 2023-09-26 | 2023-11-03 | 国家卫星海洋应用中心 | Low-orbit satellite receiving time window calculation method, device and equipment |
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| CN116609813B (en) * | 2023-05-17 | 2024-04-02 | 北京星网宇达科技股份有限公司 | Satellite orbit position determining system, method, equipment and storage medium |
| CN116996115A (en) * | 2023-09-26 | 2023-11-03 | 国家卫星海洋应用中心 | Low-orbit satellite receiving time window calculation method, device and equipment |
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