CN-116388851-B - Method, system and computer readable medium for establishing satellite-earth link of sun observation satellite

CN116388851BCN 116388851 BCN116388851 BCN 116388851BCN-116388851-B

Abstract

The invention relates to a method, a system and a computer readable medium for establishing a satellite-earth link of a sun observation satellite, wherein the method for establishing the satellite-earth link comprises the steps of establishing a sun-earth pointing coordinate system OXYZ according to a sun vector taking a satellite centroid as an origin and a normal vector of a highway surface taking the satellite centroid as the origin, wherein O represents the satellite centroid, an X axis points to the sun vector, a Y axis points to the direction of a vector obtained by cross multiplication of the normal vector of the highway surface and the sun vector, and a Z axis, the X axis and the Y axis form an orthogonal coordinate system; and controlling the posture of the satellite to be observed, so that the first included angle is kept in a first preset range, and the second included angle is kept in a second preset range, thereby enabling the satellite-to-ground link of the satellite to be effectively pointed in the whole orbit period, and improving the working reliability of the satellite to be observed.

Inventors

JIANG HU
DENG LEI
LI XINYU
CHEN BINGLONG
ZHU CHENG

Assignees

中国科学院微小卫星创新研究院
上海微小卫星工程中心

Dates

Publication Date: 20260505
Application Date: 20230419

Claims (13)

1. A method for establishing a satellite-to-earth link for a satellite in daily observation, comprising: Establishing a sun-facing direction coordinate system OXYZ according to a solar vector taking a satellite centroid as an origin and a normal vector of a ballpoint plane taking the satellite centroid as the origin, wherein O represents the satellite centroid, an X-axis points to the solar vector taking the satellite centroid as the origin, a Y-axis points to the direction of a vector obtained by cross multiplication of the normal vector of the ballpoint plane taking the satellite centroid as the origin and the solar vector taking the satellite centroid as the origin, and a Z-axis, the X-axis and the Y-axis form an orthogonal coordinate system; Calculating a first included angle and a second included angle of a beam central line of a data transmission antenna on the sun-to-sun observation satellite according to the sun-to-sun direction coordinate system OXYZ, wherein the first included angle comprises an included angle between the beam central line of the data transmission antenna and the X axis, the second included angle comprises an included angle between the beam central line of the data transmission antenna and the Z axis, and And controlling the posture of the sun-facing observation satellite, so that the first included angle is kept within a first preset range, and the second included angle is kept within a second preset range, and the satellite-ground link of the sun-facing observation satellite is enabled to be effectively pointed in the whole orbit period.
2. The method for establishing a satellite-to-earth link for a satellite under observation as claimed in claim 1, wherein said sun vector has a center of mass of the satellite as an origin According to the following formula: Wherein, the Represents a solar vector with the earth center as the origin, A satellite vector having the earth center as the origin is represented.
3. The method for establishing a satellite-to-earth link for a sun-observed satellite according to claim 2, wherein the step of establishing a sun-to-earth pointing coordinate system ozz from a sun vector having a satellite centroid as an origin and a normal vector of a highway plane having the satellite centroid as an origin comprises: Normalizing the sun vector with the satellite centroid as the origin using the following formula Obtaining normalized sun vector The normalized sun vector As the X-axis of the pair of day-pointing coordinate system ozz.
4. A method for establishing a satellite-earth link for a satellite for solar observation according to claim 3, wherein the normal vector of the orbit plane takes the center of mass of the satellite as the origin According to the following formula: Wherein, the Representing the earth position vector in the japanese coordinate system, The earth velocity vector in the japanese coordinate system is represented, and x represents the vector cross-product operation.
5. The method for establishing a satellite-to-earth link for a satellite for solar observation according to claim 4, wherein the step of establishing a coordinate system ozz for solar bearing based on a solar vector having a center of mass of the satellite as an origin and a normal vector of a highway surface having the center of mass of the satellite as an origin further comprises: normalizing the normal vector of the yellow road surface with the center of mass of the satellite as the origin by using the following formula And the sun vector taking the mass center of the satellite as the origin The vector obtained after the cross multiplication is used for obtaining a normalized cross multiplication vector Multiplying the normalized cross vector As the Y-axis of the pair of day-pointing coordinate systems ozz.
6. The method for establishing a satellite-to-earth link for a sun-observed satellite of claim 5 wherein the step of establishing a sun-to-earth pointing coordinate system ozz based on a sun vector having a satellite centroid as an origin and a normal vector of a ballast surface having a satellite centroid as an origin further comprises: orthogonalizing the normalized solar vector using the following formula And the normalized cross vector Obtaining an orthogonalized vector Orthogonalizing the vector As the Z axis of the pair of day-pointing coordinate systems ozz.
7. The method for establishing a satellite-to-earth link of a satellite for solar observation according to claim 1, wherein the data transmission antenna on the satellite for solar observation comprises a first data transmission antenna, and the step of calculating the first included angle and the second included angle of the beam center line of the data transmission antenna on the satellite for solar observation according to the coordinate system ozz for solar observation comprises: Obtaining a first direction of the first data transmission antenna beam central line in the pair of solar direction coordinate systems OXYZ, calculating a first included angle alpha 1 between the first direction and the X axis, and And calculating a second included angle beta 1 between the first direction and the reverse extension line of the Z axis.
8. The method for establishing a satellite-to-earth link for a satellite under observation according to claim 7, wherein the data antenna on the satellite under observation further comprises a second data antenna, and the step of calculating the first angle and the second angle of the beam center line of the data antenna on the satellite under observation according to the system of orientation coordinates ozz of the satellite under observation further comprises: Obtaining a second direction of the second digital antenna beam center line in the opposite-day direction coordinate system OXYZ, calculating a first included angle alpha 2 between the second direction and the reverse extension line of the X axis, and And calculating a second included angle beta 2 between the second direction and the reverse extension line of the Z axis.
9. The method for establishing a satellite-to-earth link for a solar observation satellite of claim 8, wherein the first angle α 1 and the first angle α 2 satisfy a relationship of α 1 ＝α 2 , and wherein the second angle β 1 and the second angle β 2 satisfy a relationship of β 1 ＝β 2 .
10. The method for establishing a satellite-to-earth link for a solar observation satellite of any one of claims 1-9 wherein the first predetermined range comprises 20 ° + θ 1 where θ 1 satisfies the relationship 5 ° - 1 +.10°, and the second predetermined range comprises 60 ° + θ 2 where θ 2 satisfies the relationship θ 2 ＝10°-θ 1 .
11. The method of claim 1, wherein the data transmission antenna on the satellite comprises one or more of a multi-element phased array antenna, a long wave antenna, a medium wave antenna, a short wave antenna, a directional antenna, and a non-directional antenna.
12. The satellite-ground link establishment system of the sun observation satellite is arranged in a satellite computer of the sun observation satellite, and is characterized in that the satellite-ground link establishment system comprises: A memory for storing instructions executable by the processor; A processor for executing the instructions to implement the method for establishing a satellite-to-earth link for a satellite for solar observation according to any one of claims 1-11.
13. A computer readable medium storing computer program code, which when executed by a processor implements the method of satellite-to-earth link establishment for a satellite for solar observation according to any one of claims 1-11.

Description

Method, system and computer readable medium for establishing satellite-earth link of sun observation satellite Technical Field The invention mainly relates to the technical field of satellite-to-ground link establishment of a daily observation satellite, in particular to a method, a system and a computer readable medium for establishing a satellite-to-ground link of the daily observation satellite. Background The sun is the core celestial body of the solar celestial body system, which has a decisive influence on the spatial operation of the various celestial bodies of the solar system. In recent years, the detection and observation of the sun by means of a space vehicle such as a solar observation satellite has become a hot spot for the research of astronomical objects. The solar observation satellites are provided with a Pake number, a Fu and an Quadrature parent number, wherein the Pake number can fly to the vicinity of the sun to perform an observation task, the running orbit of the Pake number is a large ellipse, the nearest near-day point is about 10 solar radiuses, the Fu and the Fu number are sun detection scientific test satellites, a telescope arranged on the Fu and Fu number can work in an H alpha wave band to continuously observe the sun, other problems caused by earth atmospheric jitter and the like can be overcome, the telescope can scan the full-day surface in a short time and image each spectrum point in a scanned wavelength range, the Quadrature parent number is a solar observation satellite specially provided for observing the sun and is provided with a hard X-ray imager for observing a solar flare non-thermal physical process, a full-day vector magnetic imager for developing solar balloon vector magnetic field imaging observation, a full-day telescope alpha solar alpha substance projection forming and early alpha telescope and other devices, and the like, wherein the full-day alpha sun comprises a Lehmann full-day plane imager, a full-sun crown telescope, a full-sun telescope, a light telescope, a guide telescope, a solar telescope and other devices, and the like devices have unique properties in the aspects of being scientific and the like. In the working process of the sun-facing observation satellite in the prior art, the satellite attitude is mainly pointed to the sun and not pointed to the ground, namely, the attitude pointed to the ground is not reserved for a satellite-ground link between the satellite and a ground station, so that an antenna beam of a data transmission antenna arranged on the sun-facing observation satellite cannot necessarily cover the ground station, and the problem that the pointed direction of the satellite-ground link possibly fails and the downlink reliability of scientific data observed by the sun-facing observation satellite is not high exists. Disclosure of Invention The application aims to solve the technical problem of providing a method, a system and a computer readable medium for establishing a satellite-to-earth link of a satellite for daily observation, which can always keep the satellite-to-earth link between the satellite for daily observation and a ground station to be effective, and improve the reliability of scientific data downlink of satellite for daily observation. The technical scheme adopted by the application for solving the technical problems is that the method for establishing the satellite-earth link of the sun observation satellite comprises the steps of establishing a sun-facing direction coordinate system OXYZ according to a solar vector taking a satellite centroid as an origin and an opposite-day direction normal vector taking the satellite centroid as the origin, wherein O represents the satellite centroid, the X-axis points to the solar vector taking the satellite centroid as the origin, the Y-axis points to the direction of a vector obtained by cross multiplication of the sun vector taking the satellite centroid as the origin and the opposite-day direction normal vector taking the satellite centroid as the origin, and the Z-axis, the X-axis and the Y-axis form an orthogonal coordinate system, calculating a first included angle and a second included angle of a beam central line of a data transmission antenna on the sun observation satellite according to the sun-facing direction coordinate system OXYZ, wherein the first included angle comprises the included angle between the beam central line of the data transmission antenna and the X-axis, the second included angle comprises the included angle between the beam central line of the data transmission antenna and the Z-axis, and controlling the gesture of the sun observation satellite so that the first included angle is kept within a first preset range, and the second included angle is kept within a second preset range, and the sun-facing direction of the satellite is effectively pointed in the whole period of the satellite. In one embodiment of the present application, the sun vector