CN114021068B - Sun synchronous circular orbit satellite sun exposure factor calculation method and device and electronic equipment - Google Patents
Sun synchronous circular orbit satellite sun exposure factor calculation method and device and electronic equipment Download PDFInfo
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Abstract
The application provides a sun-synchronous circular orbit satellite sun exposure factor calculation method, a sun-synchronous circular orbit satellite sun exposure factor calculation device and electronic equipment, which belong to the technical field of spaceflight, and the method comprises the following steps: acquiring an equatorial vector of the sun at a preset moment under an equatorial coordinate system, and acquiring a normal vector of a satellite orbit plane where a sun synchronous circular orbit satellite is located at the preset moment under the equatorial coordinate system, wherein the equatorial vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the equatorial coordinate system; based on the normal vector and the equatorial vector, obtaining an included angle between the satellite orbital plane and the equatorial vector; and obtaining sun exposure factors of the sun-synchronous circular orbit satellite based on the included angle and the orbit semi-major axis of the pre-acquired orbit of the sun-synchronous circular orbit satellite. The method does not need to calculate orbit forecast of the sun and the satellite, and does not need to calculate the time when the satellite enters and exits the earth shadow, thereby simplifying the calculation process of sun synchronous circular orbit satellite sun exposure factors, shortening the calculation time and reducing the requirements on designers.
Description
Technical Field
The application relates to the technical field of spaceflight, in particular to a sun synchronization circular orbit satellite sun exposure factor calculation method and device and electronic equipment.
Background
The calculation and analysis of the sun exposure factors of the satellite are indispensable links for the satellite orbit design, and provide basis for the design of solar panels and on-satellite power supplies. The current sun exposure factor calculation method is to perform orbit calculation according to information such as a real satellite orbit and a sun position, and obtain a satellite sun exposure factor according to the ratio of an earth shadow (i.e. a shadow projected by the earth on the atmosphere) of each circle of satellite in and out of the earth.
However, the method not only needs to calculate the orbit forecast of the sun and the satellite based on the satellite orbit, the sun position and other information (as the method for forecasting the satellite orbit in a future period of time by using the current satellite orbit measurement result and the dynamic model), but also needs to accurately calculate the satellite in-out earth shadow moment, so that the calculation process is complex, the calculation time consumption is long, the requirement on designers is high, and the calculation of the sun exposure factor of the satellite can be completed by matching with professionals.
Disclosure of Invention
The application provides a sun-synchronous circular orbit satellite sun exposure factor calculation method, a sun-synchronous circular orbit satellite sun exposure factor calculation device and electronic equipment, and aims to solve the problems that in the prior art, the calculation process for calculating the sun-synchronous circular orbit satellite sun exposure factor is complex, the calculation time consumption is long, and the requirement on designers is high.
In a first aspect, the present application provides a sun-synchronous circular orbit satellite sun exposure factor calculation method, including: acquiring an equatorial vector of the sun at a preset moment under an equatorial coordinate system, and acquiring a normal vector of a satellite orbit plane of a sun synchronous circular orbit satellite at the preset moment under the equatorial coordinate system, wherein the equatorial vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the equatorial coordinate system; obtaining an included angle between the satellite orbital plane and the equatorial vector based on the normal vector and the equatorial vector; obtaining a sun exposure factor of the sun-synchronous circular orbit satellite based on the included angle, a pre-acquired orbit semi-major axis of the orbit of the sun-synchronous circular orbit satellite and a preset formula, wherein the first preset formula is as follows:
wherein ratio represents the sun exposure factor of the sun synchronous circular orbit satellite, aeRepresents the semi-major axis of the orbit, Bangle represents the included angle between the orbital plane of the satellite and the equatorial vector, and asin represents an arcsine function.
In the embodiment of the application, the included angle between the satellite orbital plane and the equatorial vector is obtained through the equatorial vector of the sun under an equatorial coordinate system at the preset moment and the normal vector of the satellite orbital plane where the sun synchronous circular orbit satellite is located under the equatorial coordinate system at the preset moment, so that the sun exposure factor of the sun synchronous circular orbit satellite can be obtained based on the included angle, the orbit semi-major axis of the running orbit of the sun synchronous circular orbit satellite obtained in advance and a first preset formula, the orbit forecast of the sun and the satellite does not need to be calculated, the earth shadow moment of the satellite does not need to be calculated, the calculation process of the sun exposure factor of the sun synchronous circular orbit satellite is simplified, the calculation complexity is reduced, the calculation time is shortened, and the requirements on practitioners are reduced; the method for calculating the sun exposure factor of the satellite based on the sun synchronous circular orbit simplifies the complexity of coordinate conversion, thereby indirectly simplifying the calculation degree of controlling the solar sailboard and reducing the dependence on manpower calculation.
With reference to the technical solution provided by the first aspect, in some possible embodiments, the acquiring an equatorial vector of the sun at the preset time in an equatorial coordinate system includes: calculating the yellow longitude of the sun on a yellow road coordinate system at the preset moment; obtaining a ecliptic vector of the sun under the ecliptic coordinate system based on the ecliptic, wherein the ecliptic vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the ecliptic coordinate system; and obtaining the equatorial vector based on the ecliptic vector and a preset yellow-red intersection angle.
In the embodiment of the application, the ecliptic vector of the sun under the ecliptic coordinate system is obtained by presetting the ecliptic of the sun on the ecliptic coordinate system at the moment, then the ecliptic vector is converted into the equatorial vector based on the yellow-red intersection angle, the calculation process is simple, the equatorial vector can be accurately and rapidly obtained through the scheme, the accurate equatorial vector can be further provided for the follow-up calculation of the sun-synchronous circular orbit satellite sun-exposure factor, and the accuracy of the finally obtained sun-synchronous circular orbit satellite sun-exposure factor is improved.
With reference to the technical solution provided by the first aspect, in some possible implementations, the calculating the longitude of the sun on the ecliptic coordinate system at the preset time includes: acquiring the time length from the preset time to the spring point time, wherein the spring point time represents the time corresponding to the position of the sun at the spring point; and obtaining the longitude of the sun on the yellow road coordinate system at the preset moment based on the time length.
In the embodiment of the application, the time length from the preset moment to the spring minute point moment can be used for quickly and accurately obtaining the longitude of the sun on the yellow track coordinate system at the preset moment, so that accurate data can be provided for the subsequent calculation of the equator vector of the sun at the preset moment, and the equator vector can be quickly and accurately calculated.
With reference to the technical solution provided by the first aspect, in some possible implementations, the acquiring a normal vector of a satellite orbital plane of the sun-synchronous circular orbit satellite at the preset time under the equatorial coordinate system includes: and obtaining a normal vector of the orbit surface of the satellite based on the right ascension at the rising intersection point of the solar synchronous circular orbit satellite at the preset moment and a preset orbit inclination angle, wherein the preset orbit inclination angle is determined according to the pre-acquired orbit height of the solar synchronous circular orbit satellite and the orbit semi-major axis.
In the embodiment of the application, the normal vector of the orbit plane of the satellite can be rapidly and accurately calculated through the right ascension and the preset orbit inclination of the ascending intersection point of the sun-synchronous circular orbit satellite at the preset moment, so that the accurate equatorial vector is provided for the subsequent calculation of the sun-synchronous circular orbit satellite sun-exposed factor, and the accuracy of the finally obtained sun-synchronous circular orbit satellite sun-exposed factor is improved.
With reference to the technical solution provided by the first aspect, in some possible implementations, the acquiring the right ascension at the intersection point of the sun-synchronous circular orbit satellite at the preset time includes: and obtaining the descending point local time angle of the sun synchronous circular orbit satellite based on the descending point local time of the sun synchronous circular orbit satellite and a second preset formula, wherein the second preset formula is as follows:
when tod represents the descending intersection point, the value of tod is [0,24], L _ angle represents the descending intersection point local time angle, and L _ angle is an arc angle; obtaining a world time angle corresponding to the preset time based on the reduced julian day of the preset time and a third preset formula, wherein the third preset formula is as follows:
wherein t represents the preset time, Mjd (t) represents the reduced julian day of the preset time,
presentation pair
Rounding, and UTC _ angle represents a universal time angle; obtaining the right ascension of the intersection point of the sun-synchronous circular orbit satellite based on the fixed star time, the world time angle, the local time angle of the descending intersection point and a fourth preset formula corresponding to the preset time, wherein the fourth preset formula is as follows:
wherein,
when representing the fixed star corresponding to the preset time, T represents the time length from the preset time T to 1 month, 1 day and 12 days in 2000, and the unit of T is century,
and the right ascension representing the ascending intersection point of the sun-synchronous circular orbit satellite at the preset time.
In the embodiment of the application, the descending point local time angle of the sun synchronous circular orbit satellite is obtained through the descending point local time of the sun synchronous circular orbit satellite and a second preset formula; meanwhile, a world time angle corresponding to the preset time can be obtained based on the reduced julian day of the preset time and a third preset formula; then, based on the fixed star time, the world time angle, the local time angle of the descending intersection point and a fourth preset formula corresponding to the preset time, the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite can be quickly and accurately obtained, accurate data is further provided for subsequent calculation of the normal vector of the satellite orbit surface of the sun-synchronous circular orbit satellite, and therefore the normal vector of the satellite orbit surface can be quickly and accurately calculated.
With reference to the technical solution provided by the first aspect, in some possible implementations, the acquiring an orbital inclination angle of the sun-synchronous circular orbit satellite at the preset time includes: obtaining an orbit inclination angle of the solar synchronous circular orbit satellite at the preset moment according to the pre-acquired orbit height of the solar synchronous circular orbit satellite, the orbit semimajor axis and a fifth preset formula, wherein the fifth preset formula is as follows:
wherein i represents the track inclination, h represents the track height, aeRepresenting the semi-major axis of the track and acos representing the inverse cosine function.
In a second aspect, the application provides a sun-synchronous circular orbit satellite sun exposure factor calculation device, which includes an acquisition module, a first processing module and a second processing module, where the acquisition module is configured to acquire an equatorial vector of the sun in an equatorial coordinate system at a preset time, and acquire a normal vector of a satellite orbit plane of a sun-synchronous circular orbit satellite at the preset time in the equatorial coordinate system, and the equatorial vector is a unit vector pointing to a central point of the sun at the preset time from an origin of the equatorial coordinate system; the first processing module is used for obtaining an included angle between the satellite orbital plane and the equatorial vector based on the normal vector and the equatorial vector; the second processing module is used for obtaining the sun exposure factor of the sun synchronous circular orbit satellite based on the included angle, the orbit semi-major axis of the running orbit of the sun synchronous circular orbit satellite acquired in advance and a first preset formula, wherein the first preset formula is as follows:
wherein ratio represents the sun-synchronous circular orbit satelliteA sun exposure factor ofeRepresents the semi-major axis of the orbit, Bangle represents the included angle between the orbital plane of the satellite and the equatorial vector, and asin represents an arcsine function.
With reference to the technical solution provided by the second aspect, in some possible implementations, the obtaining module is further configured to calculate a longitude of the sun on a yellow-road coordinate system at the preset time; obtaining a ecliptic vector of the sun under the ecliptic coordinate system based on the ecliptic, wherein the ecliptic vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the ecliptic coordinate system; and obtaining the equatorial vector based on the ecliptic vector and a preset yellow-red intersection angle.
In some possible embodiments, the obtaining module is further configured to obtain the normal vector of the orbital plane of the satellite based on the right ascension at the intersection of the sun-synchronous circular orbit satellite at the preset time and a preset orbital inclination, and the preset orbital inclination is determined according to a pre-obtained orbital height of the sun-synchronous circular orbit satellite and the orbital semimajor axis.
In a third aspect, an embodiment of the present application provides an electronic device, including: a memory and a processor, the memory and the processor connected; the memory is used for storing programs; the processor is configured to invoke a program stored in the memory to perform a method as provided in the foregoing first aspect embodiment and/or in combination with any possible implementation manner of the foregoing first aspect embodiment.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
Fig. 1 is a schematic flowchart illustrating a method for calculating sun-synchronous circular orbit satellite sun exposure factors according to an embodiment of the present application;
FIG. 2 is a schematic diagram of the yellow-red crossing angle formed by the ecliptic coordinate system and the equatorial coordinate system shown in the embodiment of the present application;
fig. 3 is a schematic structural diagram of a sun-synchronous circular orbit satellite sun exposure factor calculation device according to an embodiment of the present application;
fig. 4 is a schematic structural diagram of an electronic device according to an embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures. Meanwhile, relational terms such as "first," "second," and the like may be used solely in the description herein to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Further, the term "and/or" in the present application is only one kind of association relationship describing the associated object, and means that three kinds of relationships may exist, for example, a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone.
The technical solution of the present application will be clearly and completely described below with reference to the accompanying drawings.
Referring to fig. 1, fig. 1 is a diagram illustrating a method for calculating a sun-synchronous circular orbit satellite sun exposure factor according to an embodiment of the present application, and the steps included in the method will be described with reference to fig. 1.
S100: the method comprises the steps of obtaining an equatorial vector of the sun under an equatorial coordinate system at a preset moment, and obtaining a normal vector of a satellite orbit plane where a sun synchronous circular orbit satellite is located under the equatorial coordinate system at the preset moment.
The equatorial vector and the normal vector in S100 may be obtained in advance and stored in a database or a disk, and may be obtained directly when needed, or may be calculated in real time when needed. The equatorial vector is a unit vector pointing from the origin of the equatorial coordinate system to the center point of the sun at a preset time.
The origin of the equatorial coordinate system is in the earth center, the X axis of the equatorial coordinate system points to the vernal point (the intersection point of the ecliptic and the equator where the sun passes from south to north), the Z axis of the equatorial coordinate system points to the north polar (the virtual center point of the rotation of the north hemisphere sky), the XY plane of the equatorial coordinate system is in the equatorial plane, and the equatorial coordinate system is a right-handed rectangular coordinate system.
The sun synchronous circular orbit satellite is a satellite with an orbit inclination angle larger than 90 degrees and passing near two poles, and the orbit plane is consistent with the direction of the sun.
In one embodiment, the process of obtaining the equatorial vector of the sun under the equatorial coordinate system at the preset time may be that, first, a longitude of the sun on a yellow road coordinate system at the preset time is calculated, then, based on the longitude, a yellow road vector of the sun under the yellow road coordinate system is obtained, the yellow road vector is a unit vector pointing from an origin of the yellow road coordinate system to a central point of the sun at the preset time, and finally, based on the yellow road vector and a preset yellow-red intersection angle, the equatorial vector is obtained. The longitude refers to the longitude of the coordinate system of the ecliptic, that is, the angle measured counterclockwise (left-handed) on the ecliptic with the spring minute point as the starting point and the celestial body as the end point. By the method, the equatorial vector can be accurately and quickly obtained, and the accurate equatorial vector can be provided for the subsequent calculation of the sun-synchronous circular orbit satellite sun-exposure factor, so that the accuracy of the finally obtained sun-synchronous circular orbit satellite sun-exposure factor is improved.
In one embodiment, the longitude of the sun on the yellow road coordinate system at the preset time may be obtained in advance and stored in a database or a magnetic disk, and may be obtained directly when needed, or may be obtained by real-time calculation when needed.
In one embodiment, the process of obtaining the longitude of the sun on the yellow road coordinate system at the preset time may be that, first, the time length from the preset time to the spring point time is obtained, and the spring point time represents the time corresponding to the position of the sun at the spring point; and then, based on the time length, the yellow longitude of the sun on the yellow road coordinate system at the preset moment can be obtained. The time length from the preset moment to the spring minute point moment can be used for quickly and accurately obtaining the longitude of the sun on the ecliptic coordinate system at the preset moment, so that accurate data can be provided for the subsequent calculation of the equator vector of the sun at the preset moment, and the equator vector can be quickly and accurately calculated.
The sun moves on the ecliptic coordinate system for one circle in one year, and the ecliptic longitude of the sun on the ecliptic coordinate system is 0 degree at the spring division point moment
Representing the yellow meridian of the sun on the yellow road coordinate system at a preset moment, and representing the preset moment by tcfWhen the preset time is the spring equinox time, the days from the preset time to the spring equinox time is days = t-tcf。
Wherein, based on the time length, the longitude of the sun on the yellow road coordinate system at the preset moment can be obtained
Obtaining, wherein 365.25 means that each turn of the sun requires one year, namely 365.25 days; 360 means that the sun turns one turn per year, i.e. 360.
The process of obtaining the ecliptic vector of the sun in the ecliptic coordinate system based on the ecliptic may be: by using
The yellow channels of the sun on the yellow road coordinate system at the preset time are expressed by
The ecliptic vector of the sun on the ecliptic coordinate system at the preset moment is represented, and the ecliptic vector of the sun on the ecliptic coordinate system
Can be calculated by the following formula:
based on the ecliptic vector and the preset yellow-red crossing angle, the process of obtaining the equatorial vector may be: by using
Expressing the equatorial vector of the sun on the equatorial coordinate system at a predetermined moment
Which means the angle of the yellow-red intersection,
the equatorial vector of the sun on the equatorial coordinate system can be calculated by the following formula:
wherein the yellow-red crossing angle
Is the angle between the OY axis of the ecliptic coordinate system and the OYo axis of the equatorial coordinate system, and is schematically shown in FIG. 2. the O-XOYoZo coordinate system shown in FIG. 2 is the equatorial coordinate system, the origin of the equatorial coordinate system is at the Earth's center, and the Xo axis points to the spring equinoxPoint, the Zo axis points to the north pole, the XoYo plane is in the equatorial plane, and the O-XoYoZo coordinate system forms a right-handed rectangular coordinate system; the O-XYZ coordinate system is a ecliptic coordinate system, the origin of the ecliptic coordinate system is positioned in the earth center, the X axis points to the spring minute point, the Z axis points to the north yellow pole (the point where the line of the ecliptic plane intersects with the virtual celestial sphere; the celestial sphere is a sphere which is concentric with the earth, has the same rotation axis and has an infinite radius and is conceived in astronomy and navigation), the XY plane is positioned in the ecliptic plane, and the O-XYZ coordinate system forms a right-handed rectangular coordinate system.
In one embodiment, the process of obtaining the normal vector of the satellite orbit plane where the sun-synchronous circular orbit satellite is located at the preset time in the equatorial coordinate system may be obtaining the normal vector of the satellite orbit plane based on the right ascension of the ascent intersection point of the sun-synchronous circular orbit satellite at the preset time and a preset orbit inclination. The normal vector of the satellite orbital plane can be quickly and accurately calculated through the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite at the preset moment and the preset orbit inclination angle, so that an accurate equatorial vector is provided for the subsequent calculation of the sun-synchronous circular orbit satellite sun-exposure factor, and the accuracy of the finally obtained sun-synchronous circular orbit satellite sun-exposure factor is improved.
The right ascension of the rising intersection point of the sun-synchronous circular orbit satellite at the preset orbit inclination angle and the preset time can be obtained in advance and stored in a database or a magnetic disk, and can be obtained directly when needed or obtained in real time or calculated when needed.
In one embodiment, the preset orbital inclination may be determined according to the orbital altitude and the orbital semimajor axis of the pre-acquired sun-synchronous circular orbit satellite: i denotes the track inclination, h denotes the track height, aeRepresenting the semi-major axis of the track, the track inclination angle can be obtained by the following formula:
where acos represents an inverse cosine function, and the orbital height h is numerically equal to the orbital semi-major axis minus the earth's radius, representing the distance between the orbit of a planet or various aircraft and its central celestial surface.
For easy understanding, a process of obtaining a normal vector of a satellite orbit plane based on a right ascension of a rising intersection point of a sun-synchronous circular orbit satellite at a preset time and a preset orbit inclination angle is given by i, and the orbit inclination angle is given by
The right ascension of the rising intersection point of the sun-synchronous circular orbit satellite at a preset time is represented, and the normal vector of the orbit plane of the satellite is represented by R, so that the normal vector of the orbit plane of the satellite can be obtained by the following formula:
in one embodiment, the process of acquiring the right ascension of the ascent intersection point of the sun-synchronous circular orbit satellite at the preset time may be that, first, a descent intersection point local time angle of the sun-synchronous circular orbit satellite is obtained based on the descent intersection point local time of the sun-synchronous circular orbit satellite; obtaining a world time angle corresponding to the preset time based on the reduced julian day of the preset time; and then obtaining the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite based on the fixed star time, the world time angle and the descending intersection point local time angle corresponding to the preset time. Obtaining a descending point local time angle of the sun synchronous circular orbit satellite through the descending point local time of the sun synchronous circular orbit satellite; meanwhile, a world time angle corresponding to the preset time can be obtained based on the reduced julian day of the preset time; then, based on the fixed star time, the world time angle and the local time angle of the descending intersection point corresponding to the preset time, the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite can be quickly and accurately obtained, accurate data is provided for subsequent calculation of the normal vector of the satellite orbit plane of the sun-synchronous circular orbit satellite, and the normal vector of the satellite orbit plane can be quickly and accurately calculated.
The right ascension means a coordinate of a celestial globe equatorial coordinate system, and means an arc section on the celestial globe between a right ascension circle passing through a spring minute point and a right ascension circle passing through a celestial body, and the right ascension is measured in a direction opposite to the celestial globe diurnal movement from the spring minute point, and the value range of the right ascension is 0h to 24 h.
The descending intersection point local time refers to the time when the orbit plane of the satellite runs from north to south and the great circle of the orbit plane forms an intersection point with the equatorial plane, and is called the descending intersection point local time.
The star time refers to a time measuring system taking the rotation period of the earth relative to the star as a reference, the time spent by the vernalization point two times of the last midday is called a star day, the star day is equal to 23 hours, 56 minutes and 4.09 seconds of the mean solar time, the moment of the vernalization point on the ground midday is taken as the starting point of the measuring system, and the vernalization time angle is used for measuring when the star time is zero.
The intersection point refers to the intersection point of the orbital plane and the earth equatorial plane of the satellite when the satellite runs from south to north.
The right ascension is a coordinate of the equatorial coordinate system, and means the arc segment on the equator between the right ascension circle passing through the spring equinox and the right ascension circle passing through the celestial body, and the right ascension varies from 0h to 24h as measured from the spring equinox in the direction opposite to the celestial movement in the daytime.
For convenience of understanding, based on the local descending intersection point of the sun-synchronous circular orbit satellite, the process of obtaining the local time angle of the descending intersection point of the sun-synchronous circular orbit satellite is obtained, where tod represents the local descending intersection point, the value range of tod is [0,24], the local time angle of the descending intersection point is represented by an angle L _ angle, and L _ angle is an arc angle, the local time angle of the descending intersection point L _ angle can be obtained by the following formula:
for convenience of understanding, based on the reduced julian day at the preset time, the process of obtaining the world time angle corresponding to the preset time is represented by t, the reduced julian day at the preset time is represented by mjd (t), and the world time angle is represented by UTC _ angle, so the world time angle UTC _ angle can be obtained by the following formula:
wherein,
presentation pair
And (6) taking the whole.
The calculation process of the reduced julian day mjd (t) is well known to those skilled in the art, and is not described herein for brevity.
In one embodiment, the obtaining process of the fixed star time corresponding to the preset time is to use
Representing fixed star time corresponding to preset time, then fixed star time
Can be obtained by the following formula:
wherein, T represents the time length from the preset time T to 1 month, 1 day, 12 years, and the unit of the time length is century, and the time length T can be obtained by the following formula:
for easy understanding, the fixed star time corresponding to the preset time is based on
A world time angle UTC _ angle and a local time angle L _ angle of a descending intersection point to obtain the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite
The right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite at the preset time is shown, and the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite at the preset time is shown
This can be obtained by the following formula:
s200: and obtaining the included angle between the satellite orbital plane and the equatorial vector based on the normal vector and the equatorial vector.
After an equatorial vector of the sun under an equatorial coordinate system at a preset moment and a normal vector of a satellite orbital plane where the sun synchronous circular orbit satellite is located under the equatorial coordinate system at the preset moment are obtained, an included angle between the satellite orbital plane and the equatorial vector can be obtained based on the normal vector and the equatorial vector.
Under the current time, the normal vector R of the satellite orbital plane of the sun synchronous circular orbit satellite and the equatorial vector of the sun
Calculating an included angle Bangle between the satellite orbital plane and the equatorial vector, wherein Bangle can be obtained by the following formula:
s300: and obtaining sun exposure factors of the sun-synchronous circular orbit satellite based on the included angle and the orbit semi-major axis of the pre-acquired orbit of the sun-synchronous circular orbit satellite.
After the included angle between the satellite orbital plane and the equatorial vector is obtained, the sun exposure factor of the sun synchronous circular orbit satellite can be quickly obtained based on the included angle and the orbit semi-major axis of the pre-acquired orbit of the sun synchronous circular orbit satellite.
For the convenience of understanding, the sun exposure factor of the sun synchronous circular orbit satellite is represented by ratio and is represented by aeRepresenting the semimajor axis of the orbit, and representing the included angle between the orbital plane of the satellite and the equatorial vector by Bangle, the sun exposure factor ratio of the sun-synchronous circular orbit satellite can be obtained by the following formula:
when the product of the cosine function value of the included angle and the semi-major axis of the orbit is more than or equal to 1, the sun exposure factor of the sun synchronous circular orbit satellite is 1; when the product of the cosine function value of the included angle and the semi-major axis of the track is less than 1,
and asin is an arcsine function.
Referring to fig. 3, fig. 3 is a diagram illustrating an apparatus 100 for calculating sun-synchronous circular orbit satellite sun exposure factors according to an embodiment of the present disclosure, which includes an obtaining module 110, a first processing module 120, and a second processing module 130.
The acquiring module 110 is configured to acquire an equatorial vector of the sun at a preset time in an equatorial coordinate system, and acquire a normal vector of a satellite orbit plane of the sun-synchronous circular orbit satellite at the preset time in the equatorial coordinate system, where the equatorial vector is a unit vector pointing to a central point of the sun at the preset time from an origin of the equatorial coordinate system.
The first processing module 120 is configured to obtain an included angle between the satellite trajectory plane and the equatorial vector based on the normal vector and the equatorial vector.
And the second processing module 130 is configured to obtain a sun exposure factor of the sun-synchronous circular orbit satellite based on the included angle and a pre-acquired orbit semi-major axis of the orbit of the sun-synchronous circular orbit satellite.
The second processing module 130 is configured to obtain a sun exposure factor of the solar synchronous circular orbit satellite based on the included angle, a pre-obtained orbit semi-major axis of the orbit of the solar synchronous circular orbit satellite, and a first preset formula, where the first preset formula is:
wherein ratio represents the sun exposure factor of the sun synchronous circular orbit satellite, aeRepresents the semi-major axis of the orbit, Bangle represents the included angle between the orbital plane of the satellite and the equatorial vector, and asin represents an arcsine function.
The obtaining module 110 is further configured to calculate a longitude of the sun on a yellow-road coordinate system at the preset time; obtaining a ecliptic vector of the sun under the ecliptic coordinate system based on the ecliptic, wherein the ecliptic vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the ecliptic coordinate system; and obtaining the equatorial vector based on the ecliptic vector and a preset yellow-red intersection angle.
The obtaining module 110 is further configured to obtain a time length from the preset time to a spring point time, where the spring point time represents a time corresponding to the position of the sun at the spring point; and obtaining the longitude of the sun on the yellow road coordinate system at the preset moment based on the time length.
The obtaining module 110 is further configured to obtain the normal vector of the satellite orbit plane based on the right ascension at the ascending intersection point of the sun-synchronous circular orbit satellite at the preset time and a preset orbit inclination, where the preset orbit inclination is determined according to the pre-obtained orbit height of the sun-synchronous circular orbit satellite and the orbit semi-major axis.
The obtaining module 110 is further configured to obtain a local time angle of a descent intersection point of the solar synchronous circular orbit satellite based on the local time of the descent intersection point of the solar synchronous circular orbit satellite; obtaining a world time angle corresponding to the preset time based on the reduced julian day of the preset time; and obtaining the right ascension of the ascending intersection point of the sun-synchronous circular orbit satellite based on the fixed star time, the world time angle and the descending intersection point local time angle corresponding to the preset time.
The obtaining module 110 is further configured to obtain the right ascension at the intersection point of the sun-synchronous circular orbit satellite at the preset time, and includes: and obtaining the descending point local time angle of the sun synchronous circular orbit satellite based on the descending point local time of the sun synchronous circular orbit satellite and a second preset formula, wherein the second preset formula is as follows:
when tod represents the descending intersection point, the value of tod is [0,24], L _ angle represents the descending intersection point local time angle, and L _ angle is an arc angle; obtaining a world time angle corresponding to the preset time based on the reduced julian day of the preset time and a third preset formula, wherein the third preset formula is as follows:
wherein t represents the preset time, Mjd (t) represents the reduced julian day of the preset time,
presentation pair
Rounding, and UTC _ angle represents a universal time angle; obtaining the right ascension of the intersection point of the sun-synchronous circular orbit satellite based on the fixed star time, the world time angle, the local time angle of the descending intersection point and a fourth preset formula corresponding to the preset time, wherein the fourth preset formula is as follows:
wherein,
to representT represents the time length from the preset time T to 1 month, 1 day and 12 days in 2000, and the unit of T is century,
and the right ascension representing the ascending intersection point of the sun-synchronous circular orbit satellite at the preset time.
The obtaining module 110 is further configured to obtain an orbital inclination of the sun-synchronous circular orbit satellite at the preset time, and includes: obtaining an orbit inclination angle of the solar synchronous circular orbit satellite at the preset moment according to the pre-acquired orbit height of the solar synchronous circular orbit satellite, the orbit semimajor axis and a fifth preset formula, wherein the fifth preset formula is as follows:
wherein i represents the track inclination, h represents the track height, aeRepresenting the semi-major axis of the track and acos representing the inverse cosine function.
The implementation principle and the generated technical effect of the sun-synchronous circular orbit satellite sun exposure factor calculation device 100 provided in the embodiment of the present application are the same as those of the foregoing sun-synchronous circular orbit satellite sun exposure factor calculation method, and for a brief description, reference may be made to corresponding contents in the foregoing sun-synchronous circular orbit satellite sun exposure factor calculation method in the foregoing embodiment, which is not mentioned in part of the embodiment of the device.
Please refer to fig. 4, which is an electronic device 200 according to an embodiment of the present disclosure. The electronic device 200 includes: a transceiver 210, a memory 220, a communication bus 230, and a processor 240.
The elements of the transceiver 210, the memory 220, and the processor 240 are electrically connected to each other directly or indirectly to achieve data transmission or interaction. For example, the components may be electrically coupled to each other via one or more communication buses 230 or signal lines. The transceiver 210 is used for transceiving data. The memory 220 is used for storing a computer program, such as a software functional module shown in fig. 3, i.e., the sun-synchronized circular orbit satellite sun exposure factor calculation apparatus 100. The sun-synchronous orbiting satellite sun exposure factor calculating apparatus 100 includes at least one software function module, which may be stored in the memory 220 in the form of software or firmware (firmware) or solidified in an Operating System (OS) of the electronic device 200. The processor 240 is configured to execute an executable module stored in the memory 220, such as a software functional module or a computer program included in the sun-synchronous circular orbit satellite sun exposure factor calculating apparatus 100. At this time, the processor 240 is configured to obtain an equatorial vector of the sun in an equatorial coordinate system at a preset time, and obtain a normal vector of a satellite orbit plane of the sun-synchronous circular orbit satellite at the preset time in the equatorial coordinate system, where the equatorial vector is a unit vector pointing to a central point of the sun at the preset time from an origin of the equatorial coordinate system; obtaining an included angle between the satellite orbital plane and the equatorial vector based on the normal vector and the equatorial vector; and obtaining the sun exposure factor of the sun synchronous circular orbit satellite based on the included angle and the orbit semi-major axis of the operation orbit of the sun synchronous circular orbit satellite acquired in advance.
The Memory 220 may be, but is not limited to, a Random Access Memory (RAM), a Read Only Memory (ROM), a Programmable Read-Only Memory (PROM), an Erasable Read-Only Memory (EPROM), an electrically Erasable Read-Only Memory (EEPROM), and the like.
The processor 240 may be an integrated circuit chip having signal processing capabilities. The Processor may be a general-purpose Processor, including a Central Processing Unit (CPU), a Network Processor (NP), and the like; but also Digital Signal Processors (DSPs), Application Specific Integrated Circuits (ASICs), Field Programmable Gate Arrays (FPGAs) or other Programmable logic devices, discrete Gate or transistor logic devices, discrete hardware components. The various methods, steps, and logic blocks disclosed in the embodiments of the present application may be implemented or performed. A general purpose processor may be a microprocessor or the processor 240 may be any conventional processor or the like.
The electronic device 200 includes, but is not limited to, a personal computer, a server, and the like.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (9)
1. A sun-synchronous circular orbit satellite sun exposure factor calculation method is characterized by comprising the following steps:
acquiring an equatorial vector of the sun at a preset moment under an equatorial coordinate system, and acquiring a normal vector of a satellite orbit plane of a sun synchronous circular orbit satellite at the preset moment under the equatorial coordinate system, wherein the equatorial vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the equatorial coordinate system;
obtaining an included angle between the satellite orbital plane and the equatorial vector based on the normal vector of the sun in the equatorial coordinate system and the equatorial vector;
obtaining a sun exposure factor of the sun-synchronous circular orbit satellite based on the included angle, a pre-acquired orbit semi-major axis of the orbit of the sun-synchronous circular orbit satellite and a first preset formula, wherein the first preset formula is as follows:
wherein ratio represents the sun exposure factor of the sun synchronous circular orbit satellite, aeRepresenting the semi-major axis of the track, Bangle representingAnd the included angle between the satellite orbital plane and the equatorial vector as represents an arcsine function.
2. The method of claim 1, wherein said obtaining an equatorial vector of the sun at a predetermined moment in time in an equatorial coordinate system comprises:
calculating the yellow longitude of the sun on a yellow road coordinate system at the preset moment;
obtaining a ecliptic vector of the sun under the ecliptic coordinate system based on the ecliptic, wherein the ecliptic vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the ecliptic coordinate system;
and based on the ecliptic vector and a preset ecliptic angle, converting the ecliptic vector of the sun under the ecliptic coordinate system into an equatorial coordinate system to obtain the equatorial vector.
3. The method according to claim 2, wherein the calculating the longitude of the sun on the ecliptic coordinate system at the preset moment comprises:
acquiring the time length from the preset time to the spring point time, wherein the spring point time represents the time corresponding to the position of the sun at the spring point;
and obtaining the longitude of the sun on the yellow road coordinate system at the preset moment based on the time length.
4. The method according to claim 1, wherein said obtaining a normal vector of a satellite orbital plane of the sun-synchronous circular orbit satellite at the predetermined time under the equatorial coordinate system comprises:
and calculating the normal vector of the orbit plane of the satellite based on the right ascension of the rising intersection point of the solar synchronous circular orbit satellite at the preset moment and a preset orbit inclination angle, wherein the preset orbit inclination angle is determined according to the pre-acquired orbit height of the solar synchronous circular orbit satellite and the orbit semi-major axis.
5. The method of claim 4, wherein obtaining the right ascension of the ascent point of the sun-synchronized circular orbit satellite at the preset time comprises:
and obtaining the descending point local time angle of the sun synchronous circular orbit satellite based on the descending point local time of the sun synchronous circular orbit satellite and a second preset formula, wherein the second preset formula is as follows:
when tod represents the descending intersection point, the value of tod is [0,24], L _ angle represents the descending intersection point local time angle, and L _ angle is an arc angle;
obtaining a world time angle corresponding to the preset time based on the reduced julian day of the preset time and a third preset formula, wherein the third preset formula is as follows:
wherein t represents the preset time, Mjd (t) represents the reduced julian day at the preset time,
presentation pair
Rounding, and UTC _ angle represents a universal time angle;
obtaining the right ascension of the intersection point of the sun-synchronous circular orbit satellite based on the fixed star time, the world time angle, the local time angle of the descending intersection point and a fourth preset formula corresponding to the preset time, wherein the fourth preset formula is as follows:
wherein,
when representing the star corresponding to the preset time,
and the right ascension representing the ascending intersection point of the sun-synchronous circular orbit satellite at the preset time.
6. The method of claim 4, wherein obtaining the orbital inclination of the sun-synchronized circular orbit satellite at the preset time comprises:
obtaining an orbit inclination angle of the solar synchronous circular orbit satellite at the preset moment according to the pre-acquired orbit height of the solar synchronous circular orbit satellite, the orbit semimajor axis and a fifth preset formula, wherein the fifth preset formula is as follows:
wherein i represents the track inclination, h represents the track height, aeRepresenting the semi-major axis of the track and acos representing the inverse cosine function.
7. A sun-synchronous circular orbit satellite sun exposure factor calculation device is characterized by comprising:
the acquisition module is used for acquiring an equatorial vector of the sun at a preset moment under an equatorial coordinate system and acquiring a normal vector of a satellite orbit plane of a sun synchronous circular orbit satellite at the preset moment under the equatorial coordinate system, wherein the equatorial vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the equatorial coordinate system;
the first processing module is used for obtaining an included angle between the satellite orbital plane and the equatorial vector based on the normal vector and the equatorial vector;
the second processing module is used for obtaining the sun exposure factor of the sun synchronous circular orbit satellite based on the included angle, the orbit semi-major axis of the running orbit of the sun synchronous circular orbit satellite acquired in advance and a first preset formula, wherein the first preset formula is as follows:
wherein ratio represents the sun exposure factor of the sun synchronous circular orbit satellite, aeRepresents the semi-major axis of the orbit, Bangle represents the included angle between the orbital plane of the satellite and the equatorial vector, and asin represents an arcsine function.
8. The device of claim 7, wherein the obtaining module is further configured to calculate a longitude of the sun on a yellow-road coordinate system at the preset time; obtaining a ecliptic vector of the sun under the ecliptic coordinate system based on the ecliptic, wherein the ecliptic vector is a unit vector pointing to the central point of the sun at the preset moment from the origin of the ecliptic coordinate system; and obtaining the equatorial vector based on the ecliptic vector and a preset yellow-red intersection angle.
9. An electronic device, comprising: a memory and a processor, the memory and the processor connected;
the memory is used for storing programs;
the processor to invoke a program stored in the memory to perform the method of any of claims 1-6.
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