CN-117682108-B - Phase difference maintaining method and system for solar synchronous satellite

CN117682108BCN 117682108 BCN117682108 BCN 117682108BCN-117682108-B

Abstract

The invention provides a phase difference maintaining method and a system of a solar synchronous satellite, which relate to the field of satellite orbit control, wherein the phase difference maintaining method comprises the steps of acquiring a plurality of groups of first operation parameter data of a first solar synchronous satellite and acquiring a plurality of groups of second operation parameter data of a second solar synchronous satellite; fitting the first operation parameter data to obtain a first flat semi-long axis trend line expression, fitting the second operation parameter data to obtain a second flat semi-long axis trend line expression, calculating a difference value to be used as a height difference trend line expression, sequentially calculating the predicted height difference of the two stars according to the height difference trend line expression, respectively performing orbit control at the epoch moment when the orbit control is started, and adjusting the actual height difference to be within a height difference threshold value so that the phase difference between the two stars is unchanged. The method can control one solar synchronous satellite in the double satellites at a certain fixed height or can realize that the height difference of the double satellites meets a certain fixed value, and realize the precise control of the orbit height.

Inventors

WU LINLIN
WU XINLIN
HE ZHENWU
Wu Linggen
CHEN QIANRU
WANG LIYING
ZHANG LINNA
PENG QIUYUE
CHI GUOHUA

Assignees

北京航天驭星科技有限公司

Dates

Publication Date: 20260508
Application Date: 20231229

Claims (10)

1. A method for maintaining a phase difference of a solar geosynchronous satellite, comprising: Step 11, aiming at a first solar synchronous satellite and a second solar synchronous satellite with unchanged phase difference and same attenuation, continuously acquiring a plurality of groups of first operation parameter data of the first solar synchronous satellite in real time after the first solar synchronous satellite enters a first operation orbit, wherein the phase difference is that the phase difference between the first solar synchronous satellite and the second solar synchronous satellite is maintained in a preset phase range; continuously acquiring a plurality of groups of second operation parameter data of the second solar synchronous satellite in real time after the second solar synchronous satellite enters a second operation orbit, wherein the second operation parameters comprise a second epoch moment and a corresponding second flat semi-long axis; step 12, fitting a plurality of groups of first operation parameter data according to the variation trend of the first flat semi-long axis along with the first epoch moment in a plurality of groups of first operation parameter data aiming at the first solar synchronous satellite to obtain a first flat semi-long axis trend line calculation formula of the first solar synchronous satellite; Fitting a plurality of groups of second operation parameter data according to the change trend of the second half long axis along with the second epoch time in a plurality of groups of second operation parameter data aiming at the second solar synchronous satellite to obtain a second half long axis trend line calculation formula of the second solar synchronous satellite; Step 13, calculating a difference value between the first flat semi-long axis trend line expression and the second flat semi-long axis trend line expression to obtain a difference value expression, wherein the difference value expression is used as a height difference trend line expression of the first solar synchronous satellite and the second solar synchronous satellite; step 14, according to the altitude difference trend line expression, calculating the predicted altitude difference between the first solar synchronous satellite and the second solar synchronous satellite at a plurality of later epoch moments in sequence; The orbit control strategy of the orbit control comprises an epoch time when the orbit control is started, an epoch time when the orbit control is ended, and altitude difference adjustment values of the first solar synchronous satellite and the second solar synchronous satellite, wherein the altitude difference adjustment values are determined according to the predicted altitude difference and the altitude difference threshold; And step 16, respectively carrying out orbit control on the first solar synchronous satellite and the second solar synchronous satellite at the epoch moment when the orbit control is started according to the orbit control strategy, and adjusting the actual height difference between the first solar synchronous satellite and the second solar synchronous satellite to be within the height difference threshold value until the epoch moment when the orbit control is ended, so that the phase difference between the first solar synchronous satellite and the second solar synchronous satellite is unchanged.
2. The method for maintaining a phase difference of a solar geosynchronous satellite according to claim 1, wherein said step 11 comprises: continuously acquiring first GNSS data representing the operation information of a first solar synchronous satellite in real time after the first solar synchronous satellite enters a first operation orbit; Calculating the first GNSS data aiming at the first solar synchronous satellite to obtain a first instantaneous root of a first operation orbit of the first solar synchronous satellite, wherein the first instantaneous root comprises a first epoch moment, a first semi-long axis, a first eccentricity, a first inclination angle, a first rising intersection point right ascent, a first near-place amplitude angle and a first even near-point angle; eliminating the corresponding short period change item from the first instantaneous root to obtain a first flat root of a first operation orbit of the first solar synchronous satellite, wherein the first flat root comprises a first epoch moment and a first flat semi-long axis; Taking a plurality of continuous first epoch moments and corresponding first flat semi-long axes as a plurality of groups of first operation parameter data of the first solar synchronous satellite; Continuously acquiring second GNSS data representing the operation information of the second solar synchronous satellite in real time after the second solar synchronous satellite enters a second operation orbit; Calculating the second GNSS data aiming at the second solar synchronous satellite to obtain a second instantaneous root of a second running orbit of the second solar synchronous satellite, wherein the second instantaneous root comprises a second epoch moment, a second semi-long axis, a second eccentricity, a second inclination angle, a second rising intersection point right ascent, a second near-place amplitude angle and a second average near-point angle; Eliminating the corresponding short period change item from the second instantaneous root to obtain a second flat root of a second running orbit of the second solar synchronous satellite, wherein the second flat root comprises a second epoch moment and a second flat semi-long axis; and taking a plurality of continuous second epoch moments and corresponding second flat semi-long axes as a plurality of groups of second operation parameter data of the second solar synchronous satellite.
3. The method of maintaining a phase difference between solar satellites according to claim 1, further comprising: After the return track control is finished, updating the next return track control to the return track control, and sequentially executing the step 14, the step 15 and the step 16; Or alternatively After the track returning control is finished, step 17 and step 18 are sequentially executed, wherein: Step 17, after the back-orbit control is finished, taking the difference between the first flat semi-long axis and the second flat semi-long axis of the same epoch time acquired in real time as a double-star height difference between the first solar synchronous satellite and the second solar synchronous satellite, calculating the average value of a plurality of groups of double-star height differences which are not smaller than a second preset duration after the back-orbit control is finished, and taking the average value of the double-star height differences as the epoch time of the next back-orbit control, wherein the predicted height difference between the first solar synchronous satellite and the second solar synchronous satellite; And 18, updating the next orbit control to the orbit control, and respectively carrying out orbit control on the first solar synchronous satellite and the second solar synchronous satellite at the epoch moment when the orbit control starts until the epoch moment when the orbit control ends, and adjusting the actual height difference between the first solar synchronous satellite and the second solar synchronous satellite to be within the height difference threshold value so that the phase difference between the first solar synchronous satellite and the second solar synchronous satellite is unchanged.
4. The method of maintaining a phase difference between solar satellites according to claim 1, further comprising: and 19, setting the lowest height thresholds of the first solar synchronous satellite and the second solar synchronous satellite to be 500km, and if the actual orbit height of any one of the first solar synchronous satellite and the second solar synchronous satellite is attenuated to 500km, directly carrying out orbit control on the solar synchronous satellite, and synchronously adjusting the actual height difference between the first solar synchronous satellite and the second solar synchronous satellite to keep the actual height difference between the first solar synchronous satellite and the second solar synchronous satellite within the height difference threshold.
5. The method of maintaining a phase difference between satellites in accordance with claim 1, comprising: Step 21, continuously acquiring a plurality of groups of third operation parameter data of the satellite in real time after the satellite enters a third operation orbit, wherein the third operation parameters comprise a third epoch moment and a corresponding third flat semi-long axis; Step 22, fitting a plurality of groups of third operation parameter data according to the variation trend of the third flat semi-long axis along with the third epoch time in the plurality of groups of third operation parameter data to obtain a third flat semi-long axis trend line calculation formula of the satellite; Step 23, according to the third flat semi-major axis trend line calculation formula, sequentially calculating the predicted flat semi-major axes of the satellites at a plurality of subsequent epoch moments, and according to the predicted flat semi-major axes of the satellites at each subsequent epoch moment, calculating the predicted orbit height of the satellite; Step 24, according to the predicted orbit height and the theoretical orbit height of the satellite at each subsequent epoch time, an orbit control strategy of the current orbit control is prepared, wherein the orbit control strategy of the current orbit control comprises epoch time when the current orbit control starts, epoch time when the current orbit control ends and an orbit height adjustment value; And step 25, according to the orbit control strategy, orbit control is carried out on the satellite at the epoch moment when the secondary orbit control starts, and the third orbit of the satellite is raised by the orbit height adjusting value until the epoch moment when the secondary orbit control ends.
6. The method for maintaining a phase difference of a solar geosynchronous satellite according to claim 5, wherein said step 21 comprises: Continuously acquiring third GNSS data representing satellite operation information in real time after the satellite enters a third operation orbit; Calculating the third GNSS data to obtain a transient root of a third running orbit of the satellite, wherein the transient root of the third running orbit comprises a third epoch moment, a third semi-long axis, a third eccentricity, a third inclination angle, a third liter intersection point right ascension, a third near-place amplitude angle and a third near-point angle; Eliminating a corresponding short period change item from the instantaneous root of the third operation orbit to obtain a flat root of the third operation orbit of the satellite, wherein the flat root of the third operation orbit comprises a third epoch moment and a third flat semi-long axis; and taking a plurality of continuous third epoch moments and corresponding third flat semi-long axes as a plurality of groups of third operation parameter data of the satellite.
7. The method of maintaining a phase difference between satellites in accordance with claim 5, further comprising: After the secondary track control is finished, updating the next track control to the secondary track control, and sequentially executing the step 23, the step 24 and the step 25; Or alternatively When the secondary track control is finished, step 26 and step 27 are sequentially performed, wherein: Step 26, when the secondary orbit control is finished, calculating the difference between a third flat semi-long axis in the third operation parameter data acquired in real time and the theoretical orbit height at the corresponding third epoch, obtaining a corresponding orbit height difference, calculating the average value of a plurality of groups of orbit height differences which are not less than a first preset duration after the secondary orbit control is finished, and taking the average value of the orbit height differences as an orbit height adjustment value to be raised by the third operation orbit of the satellite at the epoch moment when the next orbit control is finished; And step 27, updating the next orbit control to the current orbit control, orbit controlling the satellite at the epoch moment when the current orbit control starts, and raising the third orbit of the satellite by the orbit height adjustment value until the epoch moment when the current orbit control ends.
8. The method of maintaining a phase difference between satellites in accordance with claim 5, further comprising: And 28, setting the lowest elevation threshold value of the solar synchronous satellite as 500km when the satellite is the solar synchronous satellite, and directly carrying out orbit control on the solar synchronous satellite and adjusting the orbit of the solar synchronous satellite to the theoretical orbit height if the actual orbit height of the solar synchronous satellite is attenuated to 500 km.
9. A phase difference maintaining system for a solar geosynchronous satellite, comprising: The first parameter acquisition unit is used for continuously acquiring a plurality of groups of first operation parameter data of the first solar synchronous satellite in real time after the first solar synchronous satellite enters a first operation orbit aiming at the first solar synchronous satellite and the second solar synchronous satellite with the same attenuation and the phase difference is unchanged, wherein the phase difference is that the phase difference between the first solar synchronous satellite and the second solar synchronous satellite is maintained in a preset phase range; continuously acquiring a plurality of groups of second operation parameter data of the second solar synchronous satellite in real time after the second solar synchronous satellite enters a second operation orbit, wherein the second operation parameters comprise a second epoch moment and a corresponding second flat semi-long axis; The first trend line fitting unit is used for fitting a plurality of groups of first operation parameter data according to the change trend of the first flat semi-long axis along with the first epoch moment in a plurality of groups of first operation parameter data aiming at the first solar synchronous satellite to obtain a first flat semi-long axis trend line calculation formula of the first solar synchronous satellite; Fitting a plurality of groups of second operation parameter data according to the change trend of the second half long axis along with the second epoch time in a plurality of groups of second operation parameter data aiming at the second solar synchronous satellite to obtain a second half long axis trend line calculation formula of the second solar synchronous satellite; A difference value calculation formula unit is constructed and used for calculating the difference value between the first flat semi-long axis trend line calculation formula and the second flat semi-long axis trend line calculation formula to obtain a difference value calculation formula, and the difference value calculation formula is used as a height difference trend line calculation formula of the first solar synchronous satellite and the second solar synchronous satellite; The first calculating unit is used for sequentially calculating the predicted altitude difference between the first solar synchronous satellite and the second solar synchronous satellite at a plurality of later epoch moments according to the altitude difference trend line calculation formula; The first orbit control strategy formulation unit is used for formulating an orbit control strategy of the orbit control before the predicted altitude difference exceeds an altitude difference threshold value, wherein the orbit control strategy of the orbit control comprises an epoch time when the orbit control is started, an epoch time when the orbit control is ended, altitude difference adjustment values of the first solar synchronous satellite and the second solar synchronous satellite, and the altitude difference adjustment values are determined according to the predicted altitude difference and the altitude difference threshold value; The first orbit control unit is used for respectively orbit-controlling the first solar synchronous satellite and the second solar synchronous satellite at the epoch moment when the orbit returning control starts according to the orbit control strategy, and adjusting the actual height difference between the first solar synchronous satellite and the second solar synchronous satellite to be within the height difference threshold value until the epoch moment when the orbit returning control ends, so that the phase difference between the first solar synchronous satellite and the second solar synchronous satellite is unchanged.
10. The phase difference maintaining system of a solar geostationary satellite according to claim 9, comprising: The second parameter acquisition unit is used for continuously acquiring a plurality of groups of third operation parameter data of the satellite in real time after the satellite enters a third operation orbit, wherein the third operation parameters comprise a third epoch moment and a corresponding third flat semi-long axis; The second trend line fitting unit is used for fitting a plurality of groups of third operation parameter data according to the variation trend of the third flat semi-long axis along with the third epoch moment in the plurality of groups of third operation parameter data to obtain a third flat semi-long axis trend line calculation formula of the satellite; a third calculation unit, configured to sequentially calculate predicted flat semi-major axes of the satellite at a plurality of subsequent epoch times according to the third flat semi-major axis trend line calculation formula, and calculate a predicted orbit height of the satellite according to the predicted flat semi-major axes of the satellite at each subsequent epoch time; The second orbit control strategy making unit is used for making an orbit control strategy of the current orbit control according to the predicted orbit height and the theoretical orbit height of the satellite at each subsequent epoch moment, wherein the orbit control strategy of the current orbit control comprises an epoch moment when the current orbit control starts, an epoch moment when the current orbit control ends and an orbit height adjustment value; and the fourth orbit control unit is used for orbit controlling the satellite at the epoch moment when the secondary orbit control starts according to the orbit control strategy, and raising the third orbit of the satellite by the orbit height adjustment value until the epoch moment when the secondary orbit control ends.

Description

Phase difference maintaining method and system for solar synchronous satellite Technical Field The invention relates to the field of satellite orbit control, in particular to a phase difference maintaining method and a phase difference maintaining system for a solar synchronous satellite. Background A geosynchronous satellite is a satellite that operates in a geosynchronous orbit, where the plane of the satellite orbit passes through the north and south poles of the earth and moves to the east by 0.9856 degrees each day, which is exactly the angle at which the earth orbits around the sun and moves to the east each day. The satellite has the following characteristics: 1. Timing observations-the sun's synchronous orbit enables satellites to pass a specific ground point at fixed time intervals, which is important for tasks requiring timing observations, such as earth observations, weather monitoring, sea monitoring, etc. The time of each time the solar synchronous satellite passes above the earth is almost the same, so that the observed data is more comparable, and long-term trend analysis and time sequence observation are convenient to carry out. 2. Global coverage the solar synchronous orbit enables continuous observation coverage of the global world of the earth. Due to the nature of orbit, the orbital tilt angle of a solar geosynchronous satellite is typically approximately 90 degrees, so that the satellite can cover approximately the same longitude range each time it enters the hemisphere of the earth, enabling balanced observations of different regions of the earth. 3. Solar conditions-the solar synchronous orbit ensures that satellites have similar solar conditions in the earth's sky. The orbit inclination angle and the altitude of the solar synchronous satellite are accurately designed, so that the satellite can receive similar sunlight illumination in different seasons and different places, consistent illumination conditions are maintained, and the observation data is more stable and reliable. 4. And the communication and data downloading are carried out, namely the time and the position of the solar synchronous orbit above the earth are relatively fixed, so that the satellite and the ground station can communicate and download data conveniently. The satellite can timely transmit observation data, control instructions and state information, and normal acquisition and processing of the data are ensured. Therefore, many low-orbit satellites select the sun-synchronous orbit so as to be able to provide stable observation conditions and data continuity, enabling the satellites to perform their tasks more efficiently. The satellite constellation is a system for distributing a plurality of satellites at specific positions on the earth orbit, and the satellites are mutually matched to form a constellation so as to provide services such as communication, navigation, remote sensing and the like in the global scope. In order to achieve a certain task, a user will establish different phase differences for each satellite on a constellation, and the phase difference between two satellites needs to be maintained within a certain range for a long time, and once the phase difference exceeds the range, the user needs to realize orbit control. The change of the phase difference of two satellites with the same attenuation rate is determined by the orbit height difference, the larger the height difference is, the faster the phase is pulled out, the phase difference maintenance period is shortened, the orbit control frequency is increased, and the service life of the satellites is reduced. Therefore, when fine orbit control is performed on the satellite, the altitude of the satellite needs to be accurately calculated, so that the phase difference maintenance period of the satellite is prolonged. Satellites are subject to multiple types of rotational power during orbiting, which may cause deviations and changes in orbit. Common ingenuities are global non-spherical ingenuity, solar-lunar attraction, atmospheric resistance, solar light pressure, tidal force and the like. In the prior art, the representation types of satellite orbits are instantaneous roots and flat roots. The transient root refers to an orbital element of a satellite at a time, describing the position and velocity of the satellite at that time. The flat root refers to an average element obtained by performing an average process on the satellite orbit, and describes the average property of the satellite orbit. Ping Gen differ from the instantaneous root in that the flat root considers the influence of the perturbation force on the orbit, because the flat root eliminates short period change, only long period change items are considered, long period change trend of the orbit is reflected, and orbit perturbation analysis is greatly simplified, so that the flat root is often used for calculating the orbit height of the satellite. The satellite orbit height is calc