CN115271528A - Task planning method suitable for counterglow observation satellite - Google Patents
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Abstract
The invention provides a mission planning method suitable for a sun observation satellite, which comprises the following steps: and (3) taking the illumination condition as a judgment basis of the working mode, evaluating a reference coordinate system which is used by the data transmission planning on the basis, evaluating the attitude angle of the satellite relative to the ground station, calculating the attitude angle to be adjusted, and finally obtaining the optimized data transmission scheme. The method simultaneously considers the sun-oriented observation of the satellite in the sunshine area, maximizes and serializes the satellite observation as much as possible, fully utilizes the earth-oriented function of the satellite in the lunar shadow area, and preferentially arranges the data transmission task of the lunar shadow area, so that the satellite can be used safely and efficiently as far as possible under the condition of not influencing the sun-oriented observation of the satellite. The invention researches a method and a process for planning a task of a sun observation satellite, gives consideration to sun observation in a sunshine area and earth transmission in a moon shadow area, and maximizes the utilization efficiency of the satellite as much as possible.
Description
Technical Field
The invention belongs to the field of satellite application, and particularly relates to a task planning method suitable for a sun observation satellite.
Background
With the pulling of space resource stations, space targets become more and more important scientific research and application disputes, and the more space resources are occupied, the more speaking right is possessed. The sun observation is always the focus of space observation, except that various space telescopes are used for direct observation, the satellite observation is more and more concerned, the satellite observation is direct and rapid, the available time for acquiring the solar detection data is more, and a new channel is opened up for the solar observation.
The satellite in the research is supposed to adopt a low-inclination-angle elliptical orbit, and in order to improve the observation efficiency of the sun satellite, the sun satellite is generally set to be sun-oriented in a sunlight area, and earth-oriented data transmission is selected in a lunar shadow area, namely, the idle arc section of the lunar shadow area is fully utilized on the premise of not influencing the sun-observation of the satellite in the sunlight area. The sun-facing satellite observation has two key points, namely, calculating the data transmission time of the satellite, namely a data transmission arc section, and evaluating the mode supported by the current satellite according to the data transmission time and the area where the satellite is located, namely, whether the mode is single transmission or data transmission while sun-facing observation; the second calculation point is that the satellite respectively calculates the attitude angle information of the satellite in the sunshine area and the lunar shadow area, and performs attitude angle adjustment and estimation on the attitude angle information.
In the present study, because the satellite load information is sensitive, the present study does not relate to a specific load, a load coordinate system, or a specific design orbit of the satellite, and the default load coordinate system and the orbit coordinate system are completely the same as the satellite coordinate system, and are only for explaining an observation planning method for a diurnal satellite.
Disclosure of Invention
The invention aims to plan the task of the sun observation satellite, take account of sun observation in a sunshine area and earth data transmission in a moon-shadow area, and improve the sun observation efficiency and the data transmission efficiency.
The technical problem to be solved by the invention is realized by the following technical scheme:
the invention provides a task planning method suitable for a sun observation satellite, which comprises the following steps:
estimating the maximum data volume observed by a satellite on a single day according to the basic information of the satellite, and then calculating the maximum time required by single-day data transmission by combining the antenna receiving rate of a ground station;
calculating position information of the satellite in the earth center inertial coordinate system within a period of time in the future through orbit calculation according to the basic orbit information of the satellite, and calculating an available receiving arc section between a ground station and the satellite in the earth center inertial coordinate system of the satellite through orbit calculation by combining the basic information of the ground station;
thirdly, judging and marking the sunshine area and the moon shadow area of the calculated available receiving arc section, then converting a corresponding coordinate system and converting a satellite attitude angle under the corresponding coordinate system;
step four, sorting all the converted station-passing arc sections every day according to the priority, and calculating attitude angles required to be adjusted by the preselected arc sections;
selecting an optimal available receiving arc segment, judging whether the time is available or not, and adjusting and analyzing the attitude angle;
and step six, finally selecting a reasonable available receiving arc section in the day for satellite data transmission and reception.
Preferably, in the second step, the position information includes ephemeris, subsatellite point and shadow area calculation of the satellite in the time period.
Preferably, the specific step of calculating the satellite position information is:
acquiring parameters necessary for track calculation;
ephemeris calculation is conducted;
calculating the satellite points;
fourth, a photo area forecast calculation result is output.
Preferably, in the third step, the judgment method for the sunshine area and the moon-shadow area on the calculated available receiving arc segment specifically includes:
acquiring station-passing arc section information and light and shadow forecast results obtained by track calculation;
the station passing time and the station leaving time of a certain arc section span the start or end time of a moon shadow, and the satellite is considered to be in a light and shadow switching area of the moon shadow- > sunlight or sunlight- > moon shadow in the arc section;
the station passing time and the station leaving time of a certain arc section are completely in the range of the sunlight area, and the satellite is considered to be in the sunlight area in the arc section;
the station passing time and the station leaving time of a certain arc segment are completely within the moon shadow time range, and the satellite is considered to be in a moon shadow area in the arc segment.
Preferably, in the third step, a specific method for performing corresponding coordinate system conversion and converting the satellite attitude angle under the corresponding coordinate system is performed:
the arc section is positioned in the sunlight area, and converts the satellite attitude angle into star attitude angle data under a sun-oriented coordinate system;
and the arc section is positioned in a moon shadow area, and the satellite attitude angle is converted to a star body attitude angle under a body coordinate system of the geostationary satellite.
Preferably, in the fourth step, all the converted arc sections of passing the station every day are sorted according to the priority:
the station crossing arc section of the lunar shadow area, the station crossing arc section of the sunshine area, and the station crossing arc section of the light and shadow switching area;
the station-crossing arc section with long time is greater than the station-crossing arc section with short time;
the over-station arc section with small attitude angle deviation is larger than the over-station arc section with large attitude angle deviation.
Preferably, in the fourth step, the attitude angle to be adjusted for the preselected arc segment is calculated:
the preselected arc segment is longer than the data transmission time required by a single day, is positioned in the sunshine area, and needs to calculate the adjusted satellite attitude angle.
Preferably, in the fifth step, a method of selecting an optimal available receiving arc segment and judging whether the time is available is provided:
and judging whether the selected optimal available receiving arc period time conflicts with a preset ground station event, whether the use constraint of the ground station is met, and whether the use time preference of the ground station is met.
Preferably, in the fifth step, the satellite attitude angle adjustment analysis:
for the optimal arc segment available in time, which is longer than the time required for the daily data transmission and is located in the sunshine area, the adjustment of the ground orientation, the pitching angle and the side swinging angle of the arc segment is required.
Preferably, in the sixth step, a reasonable specific step of the available receiving arc segment on the day is finally selected:
the method comprises the steps of executing the arrangement of a ground station data transmission task according to the data receiving capacity of a ground station and the storage state of satellite solid memory, and generating a playback plan and a data receiving plan of the ground station;
and secondly, various constraint limits such as energy constraint, solid deposit constraint, load constraint and instruction template constraint of the satellite are considered, the planning plan is analyzed again and tested again, the data transmission plan which does not meet the constraint conditions is removed, and the safety of the satellite and a ground system is ensured.
The invention has the beneficial effects that: planning a data transmission task of a satellite, and providing a data transmission arc section processing method under a counterglow condition; three cases under satellite versus-day observation are also considered: the sunshine area is preferentially observed on days, the moon shadow area is preferentially transmitted on the ground, and the light and shadow switching area is not generally provided with tasks, so that the working efficiency of the sun observation satellite is optimized, the detection data is maximized, and the detection data is most complete.
Drawings
FIG. 1 is a block diagram of a data transmission planning process for a satellite for daily observation;
FIG. 2 is a schematic diagram of a low-inclination elliptical orbit sun observation satellite orbit simulation;
FIG. 3 is a schematic diagram of satellite-to-earth data transmission at 21/6/2022;
FIG. 4 is a schematic diagram of the relationship between the geocentric inertial coordinate system and the counterglow reference coordinate system.
Detailed Description
The invention provides a task planning method suitable for a sun observation satellite, which comprises the following steps:
estimating the maximum data volume observed by a satellite in a single day according to the basic information of the satellite, and then calculating the maximum time required by single-day data transmission by combining the antenna receiving rate of a ground station;
the calculation parameters required in the process are provided by a satellite party, the maximum data volume observed by the satellite in a single day is estimated, and the maximum time required by the data transmission in the single day is calculated by combining the antenna receiving rate of a ground station:
the satellite total day is set to generally generate the raw data (after being coded) of the daily observation of not more than 14Gbit, the receiving rate of the ground station is set to be 50Mbps, and the time required for completing data transmission under the ground orientation is 4.78min.
In the research, only the planning method of the daily observation satellite is explained, the contents of information related to the specific satellite and the ground station are not described in detail, and only the related estimation result is given.
Calculating position information of the satellite in a future period of time under the earth center inertial coordinate system according to the basic orbit information of the satellite through orbit calculation, and calculating an available receiving arc section between the earth station and the satellite under the earth center inertial coordinate system of the satellite through orbit calculation by combining with the basic information of the earth station;
the satellite basic orbit information includes: satellite name, data transmission antenna type, satellite orbit height, orbit inclination and the like; the ground station basic information comprises: longitude, latitude, elevation, antenna aperture, tracking angle range, and working angle range.
The usable receiving arc segment is the data transmission time between the ground station and the satellite, namely the station passing time under the inertial coordinate system of the satellite to the earth center.
1. The obtained position information comprises ephemeris, subsatellite points and shadow area forecast of the satellite in the time period, and the specific steps comprise:
the method comprises the steps of obtaining parameters required by track calculation, wherein the parameters comprise satellite information, receiving station information and track data;
the method comprises the following steps of calculating ephemeris, wherein ephemeris data in a certain period of time of a satellite can be extrapolated and calculated by using two types of satellite orbit data respectively;
thirdly, satellite positions are calculated by extrapolation of two types of satellite orbit data respectively, and the satellite positions of the satellites in a certain period of time can be calculated;
fourth, a photo area forecast calculation result is output.
2. Calculating an available receiving arc section between the ground station and the satellite under a satellite-to-geocentric inertial coordinate system by combining the basic information of the ground station through orbit calculation:
the satellite of the invention is supposed to adopt a low-inclination elliptical orbit, orbit information and an orbit simulation diagram are shown in fig. 2, a ground receiving station selects an X station (longitude and latitude information of the X station is set to be 34.32 degrees E and 108.10 degrees N), an elevation angle is set to be 5 degrees, a satellite data transmission beam angle range is set to be +/-67.5 degrees, and when the satellite is oriented to the sun, the data transmission availability of the satellite in one year is analyzed as follows:
TABLE 1 statistics of data transfer characteristics of satellites over a year
As can be seen from Table 1, when the satellite adopts the earth orientation, the maximum single station passing time of a single station of the ground station can reach 300.719s, i.e. 5.01min.
Thirdly, judging and marking the sunshine area and the moon shadow area of the calculated available receiving arc section, then converting a corresponding coordinate system and converting a satellite attitude angle under the corresponding coordinate system;
1. judging mark of sunshine area and moon shadow area for calculated receivable data transmission window
And obtaining the station-passing arc section information and the light shadow area forecasting result by track calculation.
The station passing time and the station leaving time of a certain arc section span the start time or the end time of a moon shadow, and the satellite is automatically oriented to the sun in the sunlight area, so that the satellite is considered to be in a sunlight switching area of the moon shadow- > sunlight or the sunlight- > moon shadow in the arc section;
the station passing time and the station leaving time of a certain arc section are completely in the range of the sunshine area, and the satellite is considered to be in the sunshine area in the arc section.
The station passing time and the station leaving time of a certain arc segment are completely within the moon shadow time range, and the satellite is considered to be in the arc moon shadow area.
Calculating a photo area, and the other time is a moon photo area; and calculating a moon shadow area, namely a light shadow area at other time, counting the moon shadow area (backlight area), counting the light shadow area (illumination area) for selecting a data transmission arc section, and acquiring more observation data.
A light and shadow switching area: under the condition that the attitude of the satellite is not forcibly adjusted, the satellite automatically rotates to the earth orientation in the arc section; sunshine areas: the satellite in the sunshine area automatically orients the sun, the satellite observes the sun, and the arc section of the sunshine area is considered to be arranged for data transmission under the condition that the moon shadow area has no proper data transmission arc section; a moon shadow area: the satellites in the moon shadow are oriented to the ground, and data transmission is preferably arranged in the arc segment, because the satellites in the moon shadow have no detection task, belong to the idle period, and can be preferentially arranged to carry out data transmission in the period.
2. Converting the corresponding coordinate system and converting the satellite attitude angle under the corresponding coordinate system
Because the position forecast and the attitude forecast are calculated under an inertial coordinate system of the earth's center, corresponding coordinate system conversion is needed to be carried out on data transmission arc sections in different areas and attitude angles of the satellite under the coordinate system are converted:
if the satellite belongs to the sunshine area, the satellite attitude angle is converted to be converted into star attitude angle data under a sun-oriented coordinate system.
And if the satellite belongs to the lunar shadow area, converting the satellite attitude angle into a satellite attitude angle under a body coordinate system of the earth orientation satellite.
In general, during the in-orbit operation of the satellite, the satellite position information downloaded by the telemetry data is directly obtained by referring to the earth-fixed coordinate system; the satellite attitude information (roll angle, pitch angle and yaw angle) downloaded from the telemetering data is data which is referred to a satellite body coordinate system, the subsequent forecasting calculation is carried out on the basis of the data, the position forecasting can be obtained by converting the telemetering positioning information under the earth-fixed coordinate system into a geocentric inertial reference system and then carrying out extrapolation calculation (the algorithm belongs to the prior mature technology and is not described in detail), and the satellite attitude forecasting is obtained by converting the telemetering attitude data under the satellite body reference system into the geocentric inertial reference system and then carrying out calculation according to a satellite orbit adjusting strategy. In the sun observation satellite researched in the project, the satellite automatically orients the sun in the sunshine area, a satellite body coordinate system is consistent with a sun reference coordinate system, satellite orbit positioning forecast information is obtained by converting telemetering positioning data under a terrestrial coordinate system into a terrestrial center inertial coordinate system and then extrapolating, and a satellite attitude angle is obtained by converting telemetering attitude data under the sun reference coordinate system into the terrestrial center inertial coordinate system and then calculating, as shown in table 2:
TABLE 2 ARC SEQUENCE PREDICTION OF PASSING OF SOURCE STATION BY SATELLITE DATA-TRANSMITTING ANTENNA IN 2022, 6-month, 21-day (Earth's heart inertial coordinate system calculation)
The earth center inertial coordinate system and the counterglow reference coordinate system have a certain conversion relation, so that the satellite orbit forecast under counterglow orientation can be obtained, and the attitude forecast data of the satellites in the sunshine area under counterglow orientation can be obtained through conversion. In a lunar shadow area, the satellite is automatically converted into orientation to the ground during the satellite station-passing period, data transmission is carried out, as shown in fig. 3, the position data obtained through remote measurement is the position of the satellite in a ground-fixed coordinate system, the satellite attitude in the remote measurement data is satellite attitude angle data in a satellite body coordinate system, and the satellite attitude angle relative to the earth center inertial coordinate can be obtained through coordinate system conversion.
It should be noted that, in general, in consideration of the safety of the satellite during the in-orbit period, in the case that the time of the arc segment of the number of passes is sufficient, the satellite itself is not considered to shake, and no attitude adjustment is performed on the satellite, that is, the yaw, pitch and yaw angles of the satellite are all 0 in an ideal state.
a. Center of earth inertial coordinate system
Inertial coordinate system of earth's center (equator) O e X e Y e Z e The J2000.0 equatorial coordinate system was used.
The origin is at the center of the earth and the reference plane is the epoch flat equator.
X e Shaft: in epoch pingPointing to the spring-divided-point direction in the equatorial plane;
Z e shaft: perpendicular to the reference plane, i.e. parallel to the mean earth spin axis;
Y e shaft: and X e 、Z e The axes form a right-hand rotating coordinate system.
b. Coordinate system of earth fixed
The earth center coordinate system which takes the earth mass center as the origin of coordinates, namely the earth center fixed connection (ECF) coordinate system, rotates with the earth. The earth adopts the WGS-84 ellipsoid model, and all height data are relative to the WGS-84 ellipsoid. Positioning data given by the GNSS is represented by the WGS-84 coordinate system.
The terrestrial coordinate system (WGS-84 coordinate system) is defined as:
origin: coinciding with the earth's centroid.
ZE shaft: pointing to the north pole;
XE axis: pointing to the intersection line of the Greenwich mean meridian plane and the equator;
YE shaft: perpendicular to the XEOZE plane, constitutes the right hand series.
c. Reference coordinate system of the day
Reference coordinate system to day: OX s Y s Z s The origin is at the star centroid.
X s Shaft: pointing to the sun direction in the ecliptic plane;
Z s shaft: perpendicular to the ecliptic plane and pointing to the north yellow pole;
Y s shaft: in the ecliptic plane with X s And vertical, constituting a right-hand coordinate system.
d. Body coordinate system (ground orientation data transmission period)
During the satellite earth orientation data transmission, the body-X axis points to the earth center, and the origin is at the center of mass of the satellite body.
OX o3 Shaft: the geocentric points to the direction of the spacecraft;
OZ o3 shaft: in the plane of the track and OX o3 The axis is vertical and points to the advancing direction of the satellite;
OY o3 shaft: perpendicular to the track plane and pointing to the negative normal direction of the track plane to form a right-hand coordinate system.
e. Coordinate system relation between coordinate systems
(1) Centroid inertial coordinate system to counterglow reference coordinate system
FIG. 3 shows a schematic diagram of the relationship between the centroid inertial coordinate system and the counterglow reference coordinate system, where E is s-i The transformation matrix from the geocentric inertial coordinate system to the counterglow reference coordinate system is as follows:
in the formula of s Is yellow-red angle, lambda s The satellite sun-vision yellow meridian is formed by the following steps that the sun-vision yellow meridian and the satellite sun-vision yellow meridian are obtained through satellite orbit information, the sun-vision yellow meridian reference coordinate system is consistent with the satellite body coordinate system during the sun-vision orientation period of the satellite, the satellite body attitude angle under the sun-vision orientation of the satellite is obtained through satellite star-sensitive data, and the satellite body attitude angle information of the satellite relative to the earth center inertia coordinate system at a certain moment can be calculated through the formula.
(2) Conversion of earth-centered inertial system to satellite body coordinate system during earth-to-earth data transmission
Let E o3-i Is a transformation matrix of the satellite body coordinate system during the earth-centered inertial system to the orbit-to-earth data transmission
Wherein u is the track amplitude angle, i is the track inclination angle, and omega is the ascent intersection right ascension. The above three data can be obtained from satellite positioning information. And the current attitude angle of the satellite can be obtained through the satellite sensitive data in the satellite telemetering data, so that the attitude angle of the satellite under the geocentric inertial system during the earth orientation can be calculated.
Step four, sorting all the converted arc sections passing the station every day according to the priority and then calculating the attitude angle of the preselected arc section needing to be adjusted;
1. sorting all the converted station-passing arc sections every day according to the priority
The station crossing arc section of the lunar shadow area, the station crossing arc section of the sunshine area, and the station crossing arc section of the light and shadow switching area;
the arc section of the station passing with long time is longer than the arc section of the station passing with short time;
the over-station arc section with small attitude angle deviation is larger than the over-station arc section with large attitude angle deviation.
2. Calculating the attitude angle of the pre-selected arc segment to be adjusted
The pre-selection arc section is longer than the data transmission time required by a single day, is positioned in a sunshine area, and needs to calculate and adjust the attitude angle of the satellite.
The method for calculating and adjusting the attitude angle refers to the steps, and daily data are supposed to be downloaded in the research, so that the use efficiency of the on-satellite memory is improved, and the timeliness of the data is ensured. Because the position forecast and the attitude forecast are calculated under the earth center inertial coordinate system, the attitude angle of the star body under the earth center inertial coordinate system is 0 by default. If the selected data transmission arc segment is longer than the data transmission time required by a single day and is in the sunshine area, the attitude angle of the adjusted satellite needs to be calculated.
For example, if 2022/6/217 in table 2 is selected to carry out data transmission in the arc segment of 2022/6/217:
TABLE 3 calculation of satellite attitude in arc segment for satellite data transmission antenna passing station in certain day
Therefore, if data transmission and reception are performed using this arc segment, the amount of adjustment of the satellite yaw should be 30.75 ° from the arrival. In the present study, considering the safety of the satellite, it is usually preferable to expand the coverage arc duration by the satellite yaw (i.e. adjustment in the X-axis direction), so the pitch (in the Z-axis direction) and yaw (in the Y-axis direction) are not considered for the moment.
Selecting an optimal available receiving arc segment, judging whether the time is available or not, and adjusting and analyzing the attitude angle;
the specific method comprises the following steps:
and selecting the optimal available receiving arc segment, preferentially selecting the longest arc segment in the moon-shaped shadow area for judgment, and judging whether the time is available, namely whether the time conflicts with a preset ground station event, whether the use constraint of the ground station is met, and whether the use time preference of the ground station is met.
If the data is not available, the arc segment is removed, and the judgment of the next data transmission arc segment is restarted until the available arc segment is selected (under the normal condition, the satellite passes the station arc segment with 6 orbits every day); if the arc segment length is available, the next judgment is carried out, whether the arc segment length is greater than or equal to the maximum data transmission length required in the current day (the calculation result of the first step) or not and whether the arc segment is in the lunar region or not are judged, if the arc segment length is greater than the maximum data transmission length required in the current day and the arc segment is located in the solar region, the data transmission arc segment needs to be subjected to ground orientation adjustment and posture angle (namely in the X, Y and Z axis directions) adjustment until the perfect data transmission arc segment in the current day is selected, and the table 4 shows that:
TABLE 4 selection and sorting results of satellite station-passing arc segments on certain day
And step six, finally selecting a reasonable available receiving data transmission arc section on the same day to be used for satellite data transmission and reception.
The method comprises the following specific steps:
the method comprises the steps of executing the arrangement of a ground station data transmission task according to the data receiving capacity of a ground station and the storage state of satellite solid memory, and generating a playback plan and a data receiving plan of the ground station;
and secondly, various constraint limits such as energy constraint, solid deposit constraint, load constraint and instruction template constraint of the satellite are considered, the planning plan is analyzed again and tested again, the data transmission plan which does not meet the constraint conditions is removed, and the safety of the satellite and a ground system is ensured.
Claims (10)
1. A task planning method suitable for a sun observation satellite is characterized by comprising the following steps:
estimating the maximum data volume observed by a satellite on a single day according to the basic information of the satellite, and then calculating the maximum time required by single-day data transmission by combining the antenna receiving rate of a ground station;
calculating position information of the satellite in a future period of time under the earth center inertial coordinate system according to the basic orbit information of the satellite through orbit calculation, and calculating an available receiving arc section between the earth station and the satellite under the earth center inertial coordinate system of the satellite through orbit calculation by combining with the basic information of the earth station;
thirdly, judging and marking the sunshine area and the moon shadow area of the calculated available receiving arc section, then converting a corresponding coordinate system and converting a satellite attitude angle under the corresponding coordinate system;
step four, sorting all the converted station-passing arc sections every day according to the priority, and calculating attitude angles required to be adjusted by the preselected arc sections;
selecting an optimal available receiving arc segment, judging whether the time is available or not, and adjusting and analyzing the attitude angle;
and step six, finally selecting a reasonable available receiving arc section on the same day for satellite data transmission and reception.
2. The mission planning method for sunward satellites of claim 1, wherein in step two, the position information comprises ephemeris, subsatellite point and shadow area calculation of the satellite in the time period.
3. The mission planning method for a diurnal observation satellite according to claim 2, wherein the step of calculating the satellite position information comprises:
acquiring parameters necessary for track calculation;
ephemeris calculation is performed;
calculating the satellite points;
fourth, a shadow area forecast calculation result is output.
4. The mission planning method applicable to a sun observation satellite according to claim 1, wherein in the third step, the judgment and identification of the sunshine area and the lunar shadow area are performed on the calculated available receiving arc segment, and the judgment method specifically comprises:
acquiring station-passing arc section information and light and shadow forecast results obtained by track calculation;
the station passing time and the station leaving time of a certain arc section span the moon shadow starting or ending time, and the satellite is considered to be in a moon shadow-sunshine or sunshine-moon shadow switching area in the arc section;
the station passing time and the station leaving time of a certain arc section are completely in the range of the sunlight area, and the satellite is considered to be in the sunlight area in the arc section;
the station passing time and the station leaving time of a certain arc segment are completely within the moon shadow time range, and the satellite is considered to be in a moon shadow area in the arc segment.
5. The mission planning method for a sunview satellite according to claim 1, wherein in step three, a specific method of converting the corresponding coordinate system and converting the attitude angle of the satellite in the corresponding coordinate system is performed:
the arc section is positioned in the sunlight area, and the satellite attitude angle is converted into star attitude angle data under a sun-oriented coordinate system;
and the arc section is positioned in a moon shadow area, and the satellite attitude angle is converted to a star body attitude angle under a body coordinate system of the geostationary satellite.
6. The mission planning method for a sunview satellite according to claim 1, wherein in step four, all the arc segments passing through the station after conversion are sorted according to priority:
the station crossing arc section of the lunar shadow area, the station crossing arc section of the sunshine area, and the station crossing arc section of the light and shadow switching area;
the station-crossing arc section with long time is greater than the station-crossing arc section with short time;
the over-station arc section with small attitude angle deviation is larger than the over-station arc section with large attitude angle deviation.
7. The mission planning method for a sunview satellite according to claim 1, wherein in the fourth step, the attitude angle to be adjusted for the preselected arc segment is calculated as follows:
the preselected arc segment is longer than the data transmission time required by a single day, is positioned in a sunshine area, and needs to calculate and adjust the attitude angle of the satellite.
8. The mission planning method for a sunview satellite according to claim 1, wherein in the fifth step, an optimal available receiving arc is selected, and whether the time is available is determined by:
and judging whether the selected optimal available receiving arc period time conflicts with a preset ground station event, whether the use constraint of the ground station is met, and whether the use time preference of the ground station is met.
9. The mission planning method for a sun observation satellite according to claim 1, wherein in the fifth step, the satellite attitude angle adjustment analysis:
for the optimal arc segment available in time, which is longer than the time required for the daily data transmission and is located in the sunshine area, the adjustment of the ground orientation, the pitching angle and the side swinging angle of the arc segment is required.
10. The mission planning method for observing satellites in view of a day according to claim 1, wherein in the sixth step, the specific step of finally selecting a reasonable available receiving arc segment on the day is:
the method comprises the steps of executing the arrangement of a ground station data transmission task according to the data receiving capacity of a ground station and the storage state of satellite solid memory, and generating a playback plan and a data receiving plan of the ground station;
and secondly, various constraint limits such as energy constraint, solid deposit constraint, load constraint and instruction template constraint of the satellite are considered, the planning plan is analyzed again and tested again, the data transmission plan which does not meet the constraint conditions is removed, and the safety of the satellite and a ground system is ensured.
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