CN107515410A - A kind of spacecraft tests checking system and method with Shuo Chuan antenna trackings earth station - Google Patents
A kind of spacecraft tests checking system and method with Shuo Chuan antenna trackings earth station Download PDFInfo
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- G—PHYSICS
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- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
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Abstract
A kind of spacecraft of the present invention tests checking system and method with Shuo Chuan antenna trackings earth station, the orbital position for the satellite that dynamics software according to receiving calculates, the attitude angle and attitude angular velocity of satellite, the number that software calculates on star passes the sensing angle of antenna, invent a kind of several biography antenna traceback earth station's algorithms and calculate the now earth station pointed by number biography antenna, and the longitude and latitude of earth station is shown in the enterprising Mobile state of monitoring software in real time, then the result of calculating and the earth station's longitude and latitude degrees of data bound in advance on star in software are compared, can real-time continuous dynamic authentication number pass the correctness of antenna traceback earth station.
Description
Technical Field
The invention relates to a test verification method for accurately tracking a ground station by a data transmission antenna for a spacecraft, which is suitable for test verification of accurately tracking the ground station by the data transmission antenna in the ground test of a spacecraft control system and belongs to the technical field of test of the spacecraft control system.
Background
The data transmission antenna is one of important components in a large remote sensing satellite load system, and the main function of the data transmission antenna is to realize high-speed down transmission of image data to a ground station. In order to effectively ensure high-speed data transmission, the beam of the antenna is narrow, and the energy attenuation outside the beam is fast, so that the antenna is required to be accurately pointed to a ground station. Particularly, when the satellite operates in an orbit service, frequent and quick small-angle maneuvering is needed, and the maneuvering angle, the orbit position, the attitude control error, the stability characteristic and the like of the satellite attitude bring great challenges to the accurate tracking of the antenna on the ground station. The control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station and sends the pointing angle to the data transmission antenna, and the data transmission antenna drives the data transmission antenna to point to the ground station according to the calculated pointing angle. Because the data transmission antenna and the control subsystem are not a development unit, the control subsystem calculates whether the pointing angle of the antenna is correct or not and verifies the pointing accuracy of the data transmission antenna, and particularly the real-time continuous verification under various working conditions in the test process of each stage of the whole satellite is an urgent problem to be solved.
In the conventional control system test, a verification method for tracking the ground station by the data transmission antenna is not published, but only briefly verified in an actual test system, and the following defects exist: 1) The data transmission antenna tracking ground station is only simple calculation at a single moment, real-time dynamic continuous verification in the whole test process cannot be implemented, and the calculation process is complicated; 2) Attitude information, orbit information and satellite maneuvering information obtained in satellite dynamics simulation cannot be fused, the calculation process is complicated, and the efficiency is low; 3) The influence of factors such as an earth ellipsoid and the like cannot be accurately considered, the calculated pointing ground station has low precision, and effective verification cannot be achieved.
Disclosure of Invention
The technical problems solved by the invention are as follows: the method overcomes the defects of the prior art, provides a test verification method for accurately tracking the ground station by the data transmission antenna for the spacecraft, and can dynamically display the error of the data transmission antenna pointing to the ground station in real time in the whole satellite test process.
The technical scheme of the invention is as follows: a test verification system for accurately tracking ground stations by a data transmission antenna for a spacecraft comprises a remote control system, a control subsystem, a data transmission antenna control module, a satellite dynamics module and a data processing module; the remote control system sends a satellite maneuvering control instruction, and the control subsystem controls the satellite platform to perform corresponding attitude maneuvering and sends the information of the actuating mechanism to the dynamics module after receiving the maneuvering control instruction; meanwhile, the control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station and sends the pointing angle to the data transmission antenna control module; the data transmission antenna control module drives the data transmission antenna to point to the ground station according to the antenna pointing angle information; the satellite dynamics module receives the information of an actuating mechanism on the satellite, simulates the satellite dynamics, outputs the real satellite attitude and orbit information and sends the information to the data transmission antenna tracking ground station calculation module; and the data processing module processes the received data and judges whether the pointing direction of the data transmission antenna can accurately track the ground station or not.
The data processing module comprises a data transmission antenna tracking ground station calculating module and a data comparing module; the data transmission antenna tracking ground station calculation module calculates the direction of the data transmission antenna in an inertial space according to the attitude and the orbit information of the satellite, calculates the direction of a vector from a geocentric to a ground station in the inertial space according to the orbit position, the earth ellipsoid information and the ground station elevation information of the satellite, calculates the longitude and latitude information of the ground station according to the earth rotation information, the earth ellipsoid information, the time difference and the nutation matrix and sends the longitude and latitude information to the data comparison module; the data comparison module compares the longitude and latitude information of the ground station with the theoretically bound ground station information, calculates to obtain the tracking error of the data transmission antenna for tracking the ground station, and if the tracking error is smaller than a set threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
A test verification method for accurately tracking ground station by data transmission antenna for spacecraft comprises the following steps:
(1) The remote control system sends a satellite maneuvering control instruction;
(2) The control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station and sends the pointing angle to the data transmission antenna control module, and the data transmission antenna control module drives the data transmission antenna to point to the ground station according to the calculated pointing angle of the antenna;
(3) The satellite dynamics module receives the information of an actuating mechanism on the satellite, simulates the satellite dynamics, outputs the real satellite attitude and orbit information and sends the information to the data transmission antenna tracking ground station calculation module;
(4) Calculating to obtain longitude and latitude information of the ground station and sending the longitude and latitude information to the data comparison module;
(5) The data comparison module compares the longitude and latitude information of the ground station with the theoretically bound ground station information, calculates to obtain the tracking error of the data transmission antenna for tracking the ground station, and if the error is smaller than a specified threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
The specific implementation process of the step (4) is as follows:
(2a) Updating related data;
(2b) Calculating a pointing vector of the data transmission antenna;
(2c) And iteratively calculating the longitude and latitude information of the ground station pointed by the data transmission antenna.
The specific implementation of the related data update in the step (2 a) is as follows:
(2a1) Calculating to obtain a Greenwich mean time angle Lamdag0 of a satellite subsatellite position according to the time and orbit information of the satellite;
(2a2) And updating the azimuth angle alpha and the pitch angle beta of the antenna pointing angle.
The specific process of calculating the pointing vector of the data transmission antenna in the step (2 b) is as follows:
(2b1) According to the time, attitude information and orbit information of the satellite, calculating to obtain a conversion matrix C of the satellite body coordinate system relative to the inertial system ib And position vector of satellite in inertial system
(2b2) According to the updated antenna pointing angles alpha and beta, an antenna installation matrix C ab Antenna installation deviation matrix C arb And a conversion matrix C ib Calculating the antenna pointing direction represented in the inertial system
Specifically, the step (2 c) of iteratively calculating the longitude and latitude information of the ground station pointed by the data transmission antenna is implemented as follows:
(2c1) According to antenna orientationAnd position vector of satellite in inertial systemCalculating to obtain an included angle between an antenna vector and a satellite-ground vector:
(2c2) Calculating to obtain an included angle theta between a ground station vector and a satellite-to-ground station vector sE The correlation equation is:
S sE ＝sin(θ sE )＝r s sin(θ sa )/r E0 ；
whereine is the eccentricity of the earth, R E Which is the radius of the earth, is,which is the latitude of the ground station, with an initial value of 0,
when S calculated sE There are a number of situations that can arise when:
when | S sE When | ≧ 1, it means that the antenna pointing direction has no intersection with the earth, and the longitude and latitude of the earth station are E λ 、If the value is 0, stopping the calculation of the period, and jumping back to the step (2 a) to calculate the next period;
when | S sE |&1, the antenna points to the ground station at the moment, and the included angle theta between the ground station vector and the satellite-ground vector at the moment is calculated rErs Comprises the following steps:
θ rErs ＝θ sE -θ sa ；
θ sE ＝sin -1 (S sE )；
(2c3) According to theta sE 、θ rErs 、And the position r of the satellite in the inertial system s Calculating and obtaining the vector from the ground station to the satellite
(2c4) According to satellite vectorAndcalculating to obtain the ground station vectorComprises the following steps:
(2c5) Converting the ground station vector into an earth fixed connection coordinate system according to a Greenwich mean vector time angle Lamdag0 of the satellite subsatellite position;
(2c6) According to the ground station vector in the earth coordinate system, calculating the longitude and latitude E of the ground station λ 、Carrying out time difference and nutation item compensation on the longitude and latitude of the ground station;
(2c7) Will be provided withSubstituting into step (2 c 2), repeating the calculation to step (2 c 6) until the calculated valueWith last calculationThe difference is less than the set threshold value, E λ (n)、I.e. the final longitude and latitude values of the ground station.
The specific implementation process of the step (5) is as follows:
the data comparison module compares the longitude and latitude information of the ground station with theoretically bound ground station information, calculates to obtain a tracking error of the data transmission antenna for tracking the ground station, and if the error is smaller than a specified threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
Compared with the prior art, the invention has the following advantages:
(1) The invention designs an algorithm for continuously tracking the ground station by the data transmission antenna in real time, and the algorithm is embedded into a test system, thereby realizing real-time dynamic continuous verification in the whole test process of the satellite, greatly enhancing the applicability and the universality and improving the working efficiency.
(2) The invention integrates attitude information, antenna pointing control information and satellite orbit information obtained by satellite dynamics simulation, attitude maneuver and attitude stability control, improves the flexibility of verification of accurate tracking of the ground station by the data transmission antenna, and greatly improves the efficiency.
(3) The method disclosed by the invention can accurately consider the influence of the earth ellipsoid factors while fusing various attitude and orbit information, effectively improve the accuracy of the ground station tracking of the data transmission antenna by adopting an iterative algorithm, and improve the accuracy of the ground station tracking verification method of the data transmission antenna.
Drawings
FIG. 1 is a schematic flow chart of the method of the present invention.
Detailed Description
The remote control system sends a satellite maneuvering control instruction; and after receiving the maneuvering control instruction, the control subsystem controls the satellite platform to perform corresponding attitude maneuvering and sends the information of the actuating mechanism to the dynamics module. And meanwhile, the control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station and sends the pointing angle to the data transmission antenna control module. The data transmission antenna control module drives the data transmission antenna to point to the ground station according to the antenna pointing angle information; the satellite dynamics module receives the information of an actuating mechanism on the satellite, simulates the satellite dynamics, outputs the real satellite attitude and orbit information and sends the information to the data transmission antenna tracking ground station calculation module; the data transmission antenna tracking ground station calculation module calculates the direction of the data transmission antenna in an inertial space according to the attitude and the orbit information of the satellite, calculates the direction of a vector from a geocentric to a ground station in the inertial space according to the orbit position, the earth ellipsoid information and the ground station elevation information of the satellite, calculates the longitude and latitude information of the ground station according to the earth rotation information, the earth ellipsoid information, the time difference and the nutation matrix and sends the longitude and latitude information to the data comparison module; the data comparison module compares the longitude and latitude information of the ground station with theoretically bound ground station information, calculates to obtain a tracking error of the data transmission antenna for tracking the ground station, and if the error is smaller than a specified threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, a test and verification method for accurately tracking a ground station by a data transmission antenna for a spacecraft includes the following steps:
(1) The remote control system sends a satellite maneuvering control instruction;
(2) The control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station, and sends the pointing angle to the data transmission antenna control module, and the data transmission antenna control module drives the data transmission antenna to point to the ground station according to the calculated pointing angle of the antenna;
(3) The satellite dynamics module receives the information of an actuating mechanism on the satellite, simulates the satellite dynamics, outputs the real satellite attitude and orbit information and sends the information to the data transmission antenna tracking ground station calculation module;
(4) After receiving the attitude and orbit information of the satellite and the pointing angle information of the antenna, the digital transmission antenna tracking ground station calculation module calculates the pointing direction of the digital transmission antenna in an inertial space according to the attitude and orbit information of the satellite, calculates the pointing direction of a vector from a geocentric to a ground station in the inertial space according to the orbit position, the earth ellipsoid information and the ground station elevation information of the satellite, calculates longitude and latitude information of the ground station according to the earth rotation information, the earth ellipsoid information, the time difference and the nutation matrix and sends the longitude and latitude information to the data comparison module;
(5) The data comparison module compares the longitude and latitude information of the ground station with the theoretically bound ground station information, calculates to obtain the tracking error of the data transmission antenna for tracking the ground station, and if the error is smaller than a specified threshold value, the set threshold value is 0.2 degrees, the data transmission antenna is considered to point to be capable of accurately tracking the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
The specific implementation of the algorithm for tracking the ground station by the antenna in the step (4) is as follows:
(2a) Calculating to obtain a Greenwich mean time angle Lamdag0 of a satellite subsatellite position according to the time and orbit information of the satellite;
(2b) Updating an azimuth angle alpha and a pitch angle beta of an antenna pointing angle;
(2c) According to the time, attitude information and orbit information of the satellite, calculating to obtain a conversion matrix C of the satellite body coordinate system relative to the inertial system ib And position vector of satellite in inertial system
(2d) According to the updated antenna pointing angles alpha and beta, an antenna installation matrix C ab Antenna installation deviation matrix C arb And a conversion matrix C ib Calculating the antenna pointing direction represented in the inertial system
(2e) According to antenna orientationAnd position vector of satellite in inertial systemCalculating to obtain an included angle between the antenna vector and the satellite-ground vector:
(2f) Calculating to obtain an included angle theta between a ground station vector and a satellite-to-ground station vector sE The correlation equation is:
S sE ＝sin(θ sE )＝r s sin(θ sa )/r E0 ；
whereine is the eccentricity of the earth, R E Which is the radius of the earth, is,which is the latitude of the ground station, with an initial value of 0,
when S is calculated sE There are a number of situations that can arise when:
when | S sE When | ≧ 1, it is explained that the antenna pointing direction has no intersection with the earth at this time, and the longitude and latitude of the ground station are E λ 、When the value is 0, stopping the calculation of the period, and jumping back to (2 a) to calculate the next period;
when | S sE |&1, the antenna points to the ground station at the moment, and the included angle theta between the ground station vector and the satellite-ground vector at the moment is calculated rErs Comprises the following steps:
θ rErs ＝θ sE -θ sa
θ sE ＝sin -1 (S sE )
proceed to the following calculation
(2g) According to theta sE 、θ rErs 、And the position r of the satellite in the inertial system s Calculating the vector from the ground station to the satellite
(2h) According to satellite vectorAndcomputable ground station vectorComprises the following steps:
(2i) Converting the ground station vector into an earth fixed connection coordinate system according to a Greenwich mean time angle Lamdag0 of the satellite subsatellite position;
(2j) Calculating the longitude and latitude E of the ground station according to the ground station vector in the earth coordinate system λ 、Compensating for the time difference and nutation terms;
(2k) Will be provided withSubstituting into (3 f), repeating the calculation to (3 j) until the calculatedWith last calculationIf the difference is less than a set threshold, here set at 0.1 degrees, then E λ (n)、The final longitude and latitude values of the ground station are obtained;
in the actual testing process, the test results are as follows (longitude of the theoretical ground station is 116.86 degrees, latitude is 40.45 degrees):
when the satellite maneuvers in the pitching axis and the rolling axis, the tracking error of the data transmission antenna for tracking the ground station is less than 0.2 degree, and the correctness of the method is verified.
In the testing process of the satellite, on one hand, different control modes exist, and the attitude control precision of the satellite in the different control modes is different; on the other hand, in the same control mode, the maneuvering angle of the data transmission antenna also changes in real time, and all the factors influence the accuracy of the data transmission antenna in tracking the ground station. The test and verification method for the accurate tracking of the data transmission antenna on the ground station can carry out real-time and dynamic verification on the direction of the antenna in the whole satellite test process; the invention integrates the technologies of satellite attitude control, attitude maneuver, orbit operation, antenna pointing, relevant ground and satellite data transmission, real-time and dynamic display of calculation results and the like, has the advantages of function, flexibility and usability and has higher degree of automation.
The invention has been applied to corresponding models and achieves good effect.
The invention has not been described in detail and is within the skill of the art.
Claims (8)
1. The utility model provides a spacecraft is with accurate ground station test verification system that trails of data transmission antenna which characterized in that: the system comprises a remote control system, a control subsystem, a data transmission antenna control module, a satellite dynamics module and a data processing module; the remote control system sends a satellite maneuvering control instruction, and the control subsystem controls the satellite platform to perform corresponding attitude maneuvering and sends the information of the actuating mechanism to the dynamics module after receiving the maneuvering control instruction; meanwhile, the control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station and sends the pointing angle to the data transmission antenna control module; the data transmission antenna control module drives the data transmission antenna to point to the ground station according to the antenna pointing angle information; the satellite dynamics module receives the information of an actuating mechanism on the satellite, simulates the satellite dynamics, outputs the real satellite attitude and orbit information and sends the information to the data transmission antenna tracking ground station calculation module; and the data processing module processes the received data and judges whether the pointing direction of the data transmission antenna can accurately track the ground station.
2. The system for testing and verifying accurate tracking of the ground station by the data transmission antenna of the spacecraft as recited in claim 1, wherein: the data processing module comprises a data transmission antenna tracking ground station calculating module and a data comparison module; the data transmission antenna tracking ground station calculation module calculates the direction of the data transmission antenna in an inertial space according to the attitude and the orbit information of the satellite, calculates the direction of a vector from a geocentric to a ground station in the inertial space according to the orbit position, the earth ellipsoid information and the ground station elevation information of the satellite, calculates the longitude and latitude information of the ground station according to the earth rotation information, the earth ellipsoid information, the time difference and the nutation matrix and sends the longitude and latitude information to the data comparison module; the data comparison module compares the longitude and latitude information of the ground station with the theoretically bound ground station information, calculates to obtain the tracking error of the data transmission antenna for tracking the ground station, and if the tracking error is smaller than a set threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
3. A test verification method for accurately tracking ground station by data transmission antenna for spacecraft is characterized by comprising the following steps:
(1) The remote control system sends a satellite maneuvering control instruction;
(2) The control subsystem calculates the pointing angle of the data transmission antenna in real time according to the orbit of the satellite, the attitude of the satellite and the information of the ground station and sends the pointing angle to the data transmission antenna control module, and the data transmission antenna control module drives the data transmission antenna to point to the ground station according to the calculated pointing angle of the antenna;
(3) The satellite dynamics module receives the information of an actuating mechanism on the satellite, simulates the satellite dynamics, outputs the real satellite attitude and orbit information and sends the information to the data transmission antenna tracking ground station calculation module;
(4) Calculating to obtain longitude and latitude information of the ground station and sending the longitude and latitude information to the data comparison module;
(5) The data comparison module compares the longitude and latitude information of the ground station with the theoretically bound ground station information, calculates to obtain the tracking error of the data transmission antenna for tracking the ground station, and if the error is smaller than a specified threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
4. The test verification method for the accurate tracking ground station of the data transmission antenna for the spacecraft as claimed in claim 3, characterized in that: the specific implementation process of the step (4) is as follows:
(2a) Updating related data;
(2b) Calculating a pointing vector of the data transmission antenna;
(2c) And iteratively calculating the longitude and latitude information of the ground station pointed by the data transmission antenna.
5. The test verification method for the accurate tracking ground station of the data transmission antenna for the spacecraft as claimed in claim 4, wherein: the specific implementation of the related data update in the step (2 a) is as follows:
(2a1) Calculating to obtain a Greenwich sidereal hour angle Lamdag0 of the satellite subsatellite position according to the time and orbit information of the satellite;
(2a2) And updating the azimuth angle alpha and the pitch angle beta of the antenna pointing angle.
6. The test verification method for the accurate tracking ground station of the data transmission antenna for the spacecraft as claimed in claim 4, wherein: the specific process of calculating the pointing vector of the data transmission antenna in the step (2 b) is as follows:
(2b1) According to the time, attitude information and orbit information of the satellite, calculating to obtain a conversion matrix C of the satellite body coordinate system relative to the inertial system ib And position vector of satellite in inertial system
(2b2) According to the updated antenna pointing angles alpha and beta, an antenna installation matrix C ab Antenna installation deviation matrix C arb And a conversion matrix C ib Calculating the antenna pointing direction represented in the inertial system
7. The test verification method for the accurate tracking ground station of the data transmission antenna for the spacecraft as claimed in claim 4, characterized in that: specifically, the step (2 c) of iteratively calculating the longitude and latitude information of the ground station pointed by the data transmission antenna is implemented as follows:
(2c1) According to antenna orientationAnd position vector of satellite in inertial systemCalculating to obtain an included angle between the antenna vector and the satellite-ground vector:
(2c2) Calculating to obtain an included angle theta between a ground station vector and a satellite-to-ground station vector sE The correlation equation is:
S sE ＝sin(θ sE )＝r s sin(θ sa )/r E0 ；
whereine is the eccentricity of the earth, R E Which is the radius of the earth, is,which is the latitude of the ground station, with an initial value of 0,
when S is calculated sE There are a number of situations that can arise when:
when | S sE When | ≧ 1, it means that the antenna pointing direction has no intersection with the earth, and the longitude and latitude of the earth station are E λ 、When the value is 0, stopping the calculation of the period, and jumping back to (2 a) to calculate the next period;
when | S sE |&1, the antenna points to the ground station at the moment, and the included angle theta between the ground station vector and the satellite-ground vector at the moment is calculated rErs Comprises the following steps:
θ rErs ＝θ sE -θ sa
θ sE ＝sin -1 (S sE )
(2c3) According to theta sE 、θ rErs 、And the position r of the satellite in the inertial system s Calculating and obtaining the vector from the ground station to the satellite
(2c4) According to satellite vectorAndcalculating to obtain the ground station vectorComprises the following steps:
(2c5) Converting the ground station vector into an earth fixed connection coordinate system according to a Greenwich mean vector time angle Lamdag0 of the satellite subsatellite position;
(2c6) According to the ground station vector in the earth coordinate system, calculating the longitude and latitude E of the ground station λ 、Carrying out time difference and nutation item compensation on the longitude and latitude of the ground station;
(2c7) Will be provided withSubstituting into step (2 c 2), repeating the calculation to step (2 c 6) until the calculated valueWith last calculationThe difference is less than the set threshold value, E λ (n)、I.e. the final longitude and latitude values of the ground station.
8. The test verification method for the accurate tracking ground station of the data transmission antenna for the spacecraft as claimed in claim 3, characterized in that: the specific implementation process of the step (5) is as follows:
the data comparison module compares the longitude and latitude information of the ground station with the theoretically bound ground station information, calculates to obtain the tracking error of the data transmission antenna for tracking the ground station, and if the error is smaller than a specified threshold value, the data transmission antenna is considered to point to accurately track the ground station; otherwise, the data transmission antenna is considered to be incapable of accurately tracking the ground station.
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