CN107515410B - A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method - Google Patents
A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method Download PDFInfo
- Publication number
- CN107515410B CN107515410B CN201710607688.3A CN201710607688A CN107515410B CN 107515410 B CN107515410 B CN 107515410B CN 201710607688 A CN201710607688 A CN 201710607688A CN 107515410 B CN107515410 B CN 107515410B
- Authority
- CN
- China
- Prior art keywords
- earth station
- antenna
- satellite
- information
- earth
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- 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
- G01S19/13—Receivers
- G01S19/23—Testing, monitoring, correcting or calibrating of receiver elements
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Computer Networks & Wireless Communication (AREA)
- Radio Relay Systems (AREA)
- Navigation (AREA)
Abstract
A kind of spacecraft of the present invention tests verifying system and method with Shuo Chuan antenna tracking earth station, according to the orbital position for the satellite that the dynamics software received calculates, the attitude angle and attitude angular velocity of satellite, the number that software calculates on star passes the direction angle of antenna, it has invented a kind of several biography antenna traceback earth station's algorithms and has calculated number at this time and passed earth station pointed by antennas, and the longitude and latitude of earth station is shown in the enterprising Mobile state of monitoring software in real time, then the earth station's longitude and latitude data bound in software on star the result of calculating and in advance are compared, can real-time continuous dynamic authentication number pass the correctness of antenna traceback earth station.
Description
Technical field
Antenna is passed with number the present invention relates to a kind of spacecraft and accurately tracks earth station's test verification method, is suitable for spacecraft
Logarithm passes the test verifying that antenna accurately tracks earth station in control system ground test, belongs to spacecraft control test skill
Art field.
Background technique
It is one of the important component in large-scale remote sensing satellite load system that number, which passes antenna, and major function is realization figure
As data high-speed under reach earth station.Wave beam for the high rate data transmission that data are effectively ensured, antenna is relatively narrow, outside wave beam
Energy attenuation is very fast, and antenna is needed accurately to be directed toward earth station.Especially satellite in-orbit service operation when need frequently it is quickly small
Angle is motor-driven, the motor-driven angle of the attitude of satellite, orbital position, attitude control error and its stability characteristic etc. all to antenna accurately with
Track earth station brings biggish challenge.Subsystem is controlled according to the track of satellite, the attitude of satellite and earth station's information, is counted in real time
It counts and passes antenna pointing angle, and be sent to number and pass antenna, number passes antenna according to calculated direction angle, and driving number passes antenna and refers to
Ground station.It is not a research institute since number passes antenna and control subsystem, controls subsystem to antenna directional angle
Calculate whether correct, number and pass the pointing accuracies of antennas and how to verify, especially in each stage test process of the whole star of satellite its
Real-time continuous verifying under various operating conditions is problem in the urgent need to address.
In previous control system test, there is not the verification method of the Shuo Chuan antenna tracking earth station published,
It is also only to carry out simple verifying, and have the disadvantage that 1) Shuo Chuan antenna tracking earth station is only in actual test macro
Be only the simple computation of single point in time, cannot implement the continuous verifying of real-time dynamic in entire test process, calculating process compared with
It is cumbersome；2) can not accomplish to merge posture information, orbit information, the motor-driven information of satellite obtained in satellite dynamics emulation,
And calculating process is cumbersome, efficiency is lower；3) factors such as consideration earth ellipsoid that can not be accurate influence, the ground of calculated direction
Precision of standing is not high, can not accomplish effectively to verify.
Summary of the invention
Present invention solves the technical problem that: the deficiencies in the prior art are overcome, a kind of spacecraft number biography antenna essence is provided
True tracking earth station tests verification method, can pass antenna direction ground by real-time, Dynamically Announce number in the overall process of satellite test
The error at face station.
Technical solution of the present invention: a kind of spacecraft passes antenna with number and accurately tracks earth station's test verifying system, including
Remote control system, control subsystem, number pass antenna control module, satellite dynamics module and data processing module；Remote control system hair
Send satellite motor-driven control instruction, after control subsystem receives maneuver autopilot instruction, control satellite platform carries out corresponding posture
It is motor-driven, and executing agency's information is sent to dynamics module；Simultaneously control subsystem according to the track of satellite, the attitude of satellite and
Earth station's information calculates number in real time and passes antenna pointing angle, and is sent to number and passes antenna control module；Number passes antenna control module
According to antenna pointing angle information, driving number passes antenna and is directed toward earth station；Satellite dynamics module receives the executing agency on star
Information emulates satellite dynamics, exports the true attitude of satellite, orbit information, and is sent to number with passing antenna tracking
Face station computing module；Data processing module handles received data, judge number pass antenna be directed toward whether can accurately with
Track earth station.
The data processing module includes Shuo Chuan antenna tracking earth station's computing module and data comparing module；Number passes antenna
Posture of earth station's computing module according to satellite, orbit information are tracked, number is calculated and passes direction of the antenna in inertial space, then
The earth's core to earth station vector is calculated in inertia according to the orbital position of satellite, earth ellipsoid information and earth station's elevation information
Finally earth station is calculated according to earth rotation information, earth ellipsoid information, the precession of the equinoxes and nutating matrix in direction in space
Latitude and longitude information is simultaneously sent to data comparing module；The ground that data comparing module binds earth station's latitude and longitude information and theory
Information of standing is compared, and the tracking error of Shuo Chuan antenna tracking earth station is calculated, if the tracking error is less than setting
Threshold value, then it is assumed that number passes antenna and is directed to accurately track earth station；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track ground
It stands.
A kind of spacecraft passes antenna with number and accurately tracks earth station's test verification method, comprises the following steps that
(1) remote control system to send the motor-driven control instruction of satellite；
(2) control subsystem calculates number in real time and passes antenna direction according to the track of satellite, the attitude of satellite and earth station's information
Angle, and be sent to number and pass antenna control module, number passes antenna control module according to calculated antenna directional angle, and driving number passes
Antenna is directed toward earth station；
(3) satellite dynamics module receives executing agency's information on star, emulates to satellite dynamics, and exports true
The attitude of satellite of reality, orbit information, and it is sent to Shuo Chuan antenna tracking earth station computing module；
(4) latitude and longitude information of earth station is calculated and is sent to data comparing module；
(5) earth station's latitude and longitude information is compared data comparing module with earth station's information of theory bookbinding, calculates
The tracking error of Shuo Chuan antenna tracking earth station is obtained, if the error is less than specified threshold value, then it is assumed that number passes antenna and is directed toward
Earth station can accurately be tracked；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track earth station.
The step (4) the specific implementation process is as follows:
(2a) related data updates；
(2b) number passes antenna pointing vector and calculates；
(2c) iterates to calculate the latitude and longitude information that number passes the earth station that antenna is directed toward.
What related data updated in the step (2a) is implemented as follows:
The time and orbit information of (2a1) according to satellite calculate the Greenwich sidereal time for obtaining sub-satellite point position
Angle LamdaG0；
(2a2) updates antenna pointing angle azimuth angle alpha and pitch angle β.
Step (2b) number passes the detailed process that antenna pointing vector calculates are as follows:
(2b1) is calculated according to the time of satellite, posture information, orbit information and is obtained satellite health coordinate system relative to used
The transition matrix C of property systemibAnd position vector of the satellite in inertial system
(2b2) installs Matrix C according to updated antenna pointing angle α, β, antennaab, antenna installation deviation Matrix CarbWith
Transition matrix Cib, calculate the antenna for obtaining and indicating in inertial system and be directed toward
Iterative calculation number passes the specific implementation of the latitude and longitude information for the earth station that antenna is directed toward such as in the step (2c)
Under:
(2c1) is directed toward according to antennaWith position vector of the satellite in inertial systemIt calculates and obtains antenna vector and star
Angle between ground vector:
(2c2) calculates the angle theta for obtaining earth station's vector and satellite to earth station's vectorsERelevant formula are as follows:
SsE=sin (θsE)=rs sin(θsa)/rE0；
WhereinE is eccentricity of the earth, REFor earth radius,
For the latitude of earth station, initial value 0,
As the S of calculatingsEThere are when following situations, it may occur in which a variety of situations:
When | SsE| when >=1, illustrates that antenna is directed toward at this time and the earth is without intersection point, set longitude, the latitude E of earth stationλ、
It is 0, and stops the calculating of this period, and jumps back to the calculating that step (2a) carries out next period；
When | SsE| when < 1, illustrate that antenna direction has earth station at this time, with calculating earth station's vector at this time and star between vector
Angle thetarErsAre as follows:
θrErs=θsE-θsa；
θsE=sin-1(SsE)；
(2c3) is according to θsE、θrErs、With position r of the satellite in inertial systems, calculate the arrow for obtaining earth station to satellite
Amount
(2c4) is according to satellite vectorWithIt calculates and obtains earth station's vectorAre as follows:
(2c5) according to the Greenwich sidereal time angle LamdaG0 of sub-satellite point position, by earth station's vector median filters to ground
Ball is connected in coordinate system；
(2c6) calculates earth station's longitude and latitude E according to earth station's vector in terrestrial coordinate systemλ、And to earth station
Longitude and latitude carries out the precession of the equinoxes and the compensation of nutating item；
(2c7) willIt brings into step (2c2), computes repeatedly to step (2c6), until calculatedWith last time
It calculatesDifference is less than the threshold value of setting, then Eλ(n)、As earth station's final longitude and latitude value.
The step (5) the specific implementation process is as follows:
Earth station's latitude and longitude information is compared data comparing module with earth station's information of theory bookbinding, is calculated
The tracking error of Shuo Chuan antenna tracking earth station, if the error is less than specified threshold value, then it is assumed that number passes antenna and is directed to
Accurate tracking earth station；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track earth station.
The invention has the following advantages over the prior art:
(1) present invention devises a kind of several algorithms for passing antenna real-time continuous tracking earth station, and the algorithm is embedded into
In test macro, the continuous verifying of real-time dynamic in the entire test process of satellite is realized, applicability and versatility greatly enhance,
It improves work efficiency.
(2) present invention merged satellite dynamics emulation, attitude maneuver and pose stabilization control posture information obtained,
Antenna pointing control information, satellite-orbit information improve number and pass the flexibility that antenna accurately tracks earth station's verifying, and efficiency is big
It is big to improve.
(3) present invention accurately considers the influence of earth ellipsoid factor while merging various postures and orbit information, and
The precision that Shuo Chuan antenna tracking earth station is effectively improved using iterative algorithm improves Shuo Chuan antenna tracking earth station authentication
The accuracy of method.
Detailed description of the invention
Fig. 1 is method flow schematic diagram of the invention.
Specific embodiment
Remote control system sends the motor-driven control instruction of satellite；After control subsystem receives maneuver autopilot instruction, satellite is controlled
Platform carries out corresponding attitude maneuver, and executing agency's information is sent to dynamics module.Subsystem is controlled simultaneously according to defending
Track, the attitude of satellite and the earth station's information of star calculate number in real time and pass antenna pointing angle, and is sent to number and passes day line traffic control mould
Block.Number passes antenna control module according to antenna pointing angle information, and driving number passes antenna and is directed toward earth station；Satellite dynamics module
Executing agency's information on star is received, satellite dynamics is emulated, exports the true attitude of satellite, orbit information, concurrently
Give Shuo Chuan antenna tracking earth station computing module；Posture of the Shuo Chuan antenna tracking earth station's computing module according to satellite, track
Information calculates number and passes direction of the antenna in inertial space, then according to the orbital position of satellite, earth ellipsoid information and ground
Direction of the earth's core to the earth station vector in inertial space is calculated in elevation information of standing, finally according to earth rotation information,
Ball ellipsoid information, the precession of the equinoxes and nutating matrix are calculated the latitude and longitude information of earth station and are sent to data comparing module；Data
Earth station's latitude and longitude information is compared comparison module with earth station's information of theory bookbinding, and number is calculated and passes antenna tracking
The tracking error of earth station, if the error is less than specified threshold value, then it is assumed that number passes antenna and is directed to accurately track ground
It stands；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track earth station.
The present invention is described in detail with reference to the accompanying drawing.
It is comprised the following steps that as shown in Figure 1, a kind of spacecraft accurately tracks earth station's test verification method with number biography antenna
(1) remote control system sends the motor-driven control instruction of satellite；
(2) control subsystem calculates number in real time and passes antenna direction according to the track of satellite, the attitude of satellite and earth station's information
Angle, and be sent to number and pass antenna control module, number passes antenna control module according to calculated antenna directional angle, and driving number passes
Antenna is directed toward earth station；
(3) satellite dynamics module receives executing agency's information on star, emulates to satellite dynamics, and exports true
The attitude of satellite of reality, orbit information, and it is sent to Shuo Chuan antenna tracking earth station computing module；
(4) when receive satellite posture and orbit information, antenna pointing angle information after, Shuo Chuan antenna tracking earth station
Posture of the computing module according to satellite, orbit information calculate number and pass direction of the antenna in inertial space, then according to satellite
Finger of the earth's core to the earth station vector in inertial space is calculated in orbital position, earth ellipsoid information and earth station's elevation information
To the latitude and longitude information of earth station is finally calculated according to earth rotation information, earth ellipsoid information, the precession of the equinoxes and nutating matrix
And it is sent to data comparing module；
(5) earth station's latitude and longitude information is compared data comparing module with earth station's information of theory bookbinding, calculates
The tracking error of Shuo Chuan antenna tracking earth station is obtained, if the error is less than specified threshold value, given threshold is 0.2 here
Degree, then it is assumed that number passes antenna and is directed to accurately track earth station；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track ground
It stands.
Antenna tracking earth station algorithm is implemented as follows in the step (4):
The time and orbit information of (2a) according to satellite calculate the Greenwich sidereal time angle for obtaining sub-satellite point position
LamdaG0；
(2b) updates antenna pointing angle azimuth angle alpha and pitch angle β；
(2c) is calculated according to the time of satellite, posture information, orbit information and is obtained satellite health coordinate system relative to inertia
The transition matrix C of systemibAnd position vector of the satellite in inertial system
(2d) installs Matrix C according to updated antenna pointing angle α, β, antennaab, antenna installation deviation Matrix CarbWith
Transition matrix Cib, calculate the antenna for obtaining and indicating in inertial system and be directed toward
(2e) is directed toward according to antennaWith position vector of the satellite in inertial systemIt calculates with obtaining antenna vector and star
Angle between vector:
(2f) calculates the angle theta for obtaining earth station's vector and satellite to earth station's vectorsERelevant formula are as follows:
SsE=sin (θsE)=rs sin(θsa)/rE0；
WhereinE is eccentricity of the earth, REFor earth radius,
For the latitude of earth station, initial value 0,
As the S of calculatingsEThere are when following situations, it may occur in which a variety of situations:
When | SsE| when >=1, illustrates that antenna is directed toward at this time and the earth is without intersection point, set longitude, the latitude E of earth stationλ、
It is 0, and stops the calculating of this period, and jumps back to the calculating that (2a) carries out next period；
When | SsE| when < 1, illustrate that antenna direction has earth station at this time, with calculating earth station's vector at this time and star between vector
Angle thetarErsAre as follows:
θrErs=θsE-θsa
θsE=sin-1(SsE)
Continue following calculating
(2g) is according to θsE、θrErs、With position r of the satellite in inertial systems, the vector of calculating earth station to satellite
(2h) is according to satellite vectorWithCalculably face station vectorAre as follows:
(2i) will be arrived earth station's vector median filters at this time according to the Greenwich sidereal time angle LamdaG0 of sub-satellite point position
The earth is connected in coordinate system；
(2j) calculates earth station longitude and latitude E at this time according to earth station's vector in terrestrial coordinate systemλ、And to year
Difference and nutating item compensate；
(2k) willIt brings into (3f), computes repeatedly to (3j), until calculatedWith last computationDifference is less than the threshold value of setting, and given threshold is 0.1 degree here, then Eλ(n)、As earth station is final
Longitude and latitude value；
In actual test process, test result is following, and (longitude of theoretical earth station is 116.86 degree, and latitude is
40.45 degree):
When satellite is when pitch axis and the axis of rolling carry out motor-driven, the tracking error of Shuo Chuan antenna tracking earth station is less than 0.2
Degree, demonstrates the correctness of this method.
During the test, on the one hand there are different control models in satellite, the gesture stability of satellite under different control models
There are difference for precision；On the other hand under same control model, number pass antennas motor-driven angles also change in real time, these because
Element all influences the precision of Shuo Chuan antenna tracking earth station.Number biography antenna accurately tracks earth station's test verification method and can defend
Star tests in overall process real-time, the dynamic authentication for carrying out antenna direction；The present invention combine satellite gravity anomaly, attitude maneuver,
Track operation, antenna be directed toward, data transmission, calculated result in real time and the technologies such as Dynamically Announce, are taken into account on relevant ground and star
Function, flexibility and ease for use, and the degree of automation with higher.
The present invention has been applied in corresponding model, and achieves good effect.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (6)
1. a kind of spacecraft with number pass antenna accurately track earth station test verifying system, it is characterised in that: including remote control system,
Control subsystem, number passes antenna control module, satellite dynamics module and data processing module；It is motor-driven that remote control system sends satellite
Control instruction, after control subsystem receives maneuver autopilot instruction, control satellite platform carries out corresponding attitude maneuver, and will hold
Row organization information is sent to dynamics module；Subsystem is controlled simultaneously according to the track of satellite, the attitude of satellite and earth station's information,
Number is calculated in real time and passes antenna pointing angle, and is sent to number and is passed antenna control module；Number passes antenna control module and is referred to according to antenna
To angle information, driving number passes antenna and is directed toward earth station；Satellite dynamics module receives executing agency's information on star, to satellite
Dynamics is emulated, and exports the true attitude of satellite, orbit information, and be sent to data processing module；Data processing module
Received data are handled, judge that number passes whether antenna direction can accurately track earth station；
The data processing module includes Shuo Chuan antenna tracking earth station's computing module and data comparing module；Number passes antenna tracking
Posture of earth station's computing module according to satellite, orbit information calculate number and pass direction of the antenna in inertial space, then basis
The earth's core to earth station vector is calculated in inertial space in orbital position, earth ellipsoid information and the earth station's elevation information of satellite
In direction, the longitude and latitude of earth station is finally calculated according to earth rotation information, earth ellipsoid information, the precession of the equinoxes and nutating matrix
Degree information is simultaneously sent to data comparing module；Data comparing module believes the earth station of earth station's latitude and longitude information and theoretical bookbinding
Breath is compared, and the tracking error of Shuo Chuan antenna tracking earth station is calculated, if the tracking error is less than the threshold value of setting,
Then think that number passes antenna and is directed to accurately track earth station；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track earth station.
2. a kind of spacecraft passes antenna with number and accurately tracks earth station's test verification method, it is characterised in that comprise the following steps that
(1) remote control system to send the motor-driven control instruction of satellite；
(2) control subsystem calculates number in real time and passes antenna directional angle according to the track of satellite, the attitude of satellite and earth station's information
Degree, and be sent to number and pass antenna control module, number passes antenna control module according to calculated antenna directional angle, and driving number passes day
Line is directed toward earth station；
(3) satellite dynamics module receives executing agency's information on star, emulates to satellite dynamics, and exports true
The attitude of satellite, orbit information, and it is sent to Shuo Chuan antenna tracking earth station computing module；
(4) latitude and longitude information of earth station is calculated and is sent to data comparing module, specifically:
Posture of the Shuo Chuan antenna tracking earth station's computing module according to satellite, orbit information calculate number and pass antenna in inertial space
In direction, then according to the orbital position of satellite, earth ellipsoid information and earth station's elevation information be calculated the earth's core to ground
Direction of the face station vector in inertial space, finally according to earth rotation information, earth ellipsoid information, the precession of the equinoxes and nutating matrix meter
It calculates the latitude and longitude information for obtaining earth station and is sent to data comparing module；
(5) earth station's latitude and longitude information is compared data comparing module with earth station's information of theory bookbinding, is calculated
The tracking error of Shuo Chuan antenna tracking earth station, if the error is less than specified threshold value, then it is assumed that number passes antenna and is directed to
Accurate tracking earth station；Otherwise, then it is assumed that number, which passes antenna, cannot accurately track earth station.
3. a kind of spacecraft according to claim 2 passes antenna with number and accurately tracks earth station's test verification method, special
Sign is: the step (4) the specific implementation process is as follows:
(2a) related data updates；
(2b) number passes antenna pointing vector and calculates；
(2c) iterates to calculate the latitude and longitude information that number passes the earth station that antenna is directed toward.
4. a kind of spacecraft according to claim 3 passes antenna with number and accurately tracks earth station's test verification method, special
Sign is: what related data updated in the step (2a) is implemented as follows:
The time and orbit information of (2a1) according to satellite calculate the Greenwich sidereal time angle for obtaining sub-satellite point position
LamdaG0；
(2a2) updates antenna pointing angle azimuth angle alpha and pitch angle β.
5. a kind of spacecraft according to claim 3 passes antenna with number and accurately tracks earth station's test verification method, special
Sign is: step (2b) number passes the detailed process that antenna pointing vector calculates are as follows:
(2b1) is calculated according to the time of satellite, posture information, orbit information and is obtained satellite health coordinate system relative to inertial system
Transition matrix CibAnd position vector of the satellite in inertial system
(2b2) installs Matrix C according to updated antenna pointing angle α, β, antennaab, antenna installation deviation Matrix CarbAnd conversion
Matrix Cib, calculate the antenna for obtaining and indicating in inertial system and be directed toward
6. a kind of spacecraft according to claim 3 passes antenna with number and accurately tracks earth station's test verification method, special
Sign is: iterative calculation number passes the specific implementation of the latitude and longitude information for the earth station that antenna is directed toward such as in the step (2c)
Under:
(2c1) is directed toward according to antennaWith position vector of the satellite in inertial systemIt calculates and swears with obtaining antenna vector and star
Angle between amount:
(2c2) calculates the angle theta for obtaining earth station's vector and satellite to earth station's vectorsERelevant formula are as follows:
SsE=sin (θsE)=rssin(θsa)/rE0；
WhereinE is eccentricity of the earth, REFor earth radius,For ground
The latitude at face station, initial value 0,Position of the rs satellite in inertial system；
As the S of calculatingsEThere are when following situations, it may occur in which a variety of situations:
When | SsE| when >=1, illustrates that antenna is directed toward at this time and the earth is without intersection point, set longitude, the latitude E of earth stationλ、It is 0,
And stop the calculating of this period, and jump back to the calculating that (2a) carries out next period；
When | SsE| when < 1, illustrate that antenna direction has earth station at this time, with calculating earth station's vector at this time and star the folder between vector
Angle θrErsAre as follows:
θrErs=θsE-θsa
θsE=sin-1(SsE)
(2c3) is according to θsE、θrErs、With position r of the satellite in inertial systems, calculate the vector for obtaining earth station to satellite
(2c4) is according to satellite vectorWithIt calculates and obtains earth station's vectorAre as follows:
(2c5) consolidates earth station's vector median filters to the earth according to the Greenwich sidereal time angle LamdaG0 of sub-satellite point position
Even in coordinate system；
(2c6) calculates earth station's longitude and latitude E according to earth station's vector in terrestrial coordinate systemλ、And to the longitude and latitude of earth station
Degree carries out the precession of the equinoxes and the compensation of nutating item；
(2c7) willIt brings into step (2c2), computes repeatedly to step (2c6), until calculatedWith last computation
'sDifference is less than the threshold value of setting, then Eλ(n)、As earth station's final longitude and latitude value.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710607688.3A CN107515410B (en) | 2017-07-24 | 2017-07-24 | A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710607688.3A CN107515410B (en) | 2017-07-24 | 2017-07-24 | A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107515410A CN107515410A (en) | 2017-12-26 |
| CN107515410B true CN107515410B (en) | 2019-08-09 |
Family
ID=60722455
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710607688.3A Active CN107515410B (en) | 2017-07-24 | 2017-07-24 | A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107515410B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109194380B (en) * | 2018-09-07 | 2021-06-18 | 北京空间技术研制试验中心 | Measurement and control communication support system for space target detector |
| CN109547094A (en) * | 2018-12-06 | 2019-03-29 | 安徽站乾科技有限公司 | A kind of ground station tracking based on satellite communication |
| CN109781059B (en) * | 2019-01-08 | 2021-05-11 | 上海卫星工程研究所 | Satellite-borne point beam antenna pointing to ground precision evaluation system |
| CN110531636B (en) * | 2019-08-16 | 2022-07-29 | 北京控制工程研究所 | Ground dynamics software and satellite software combined rapid simulation test method |
| CN111483615B (en) * | 2020-04-17 | 2021-06-29 | 中国科学院微小卫星创新研究院 | Method for realizing pointing posture of quantum satellite to ground optical station |
| CN112468211B (en) * | 2020-10-30 | 2023-02-28 | 西安空间无线电技术研究所 | Tracking antenna on-orbit pointing error correction method and space-based measurement and control communication system |
| CN112666988B (en) * | 2020-12-15 | 2022-10-25 | 上海卫星工程研究所 | Two-dimensional pointing mechanism installation and photoelectric axis pointing deviation correction method and system |
| CN112666847A (en) * | 2021-03-18 | 2021-04-16 | 长沙天仪空间科技研究院有限公司 | Satellite test system and method suitable for various simulation states |
| CN115811712A (en) * | 2021-09-13 | 2023-03-17 | 海鹰航空通用装备有限责任公司 | Antenna guiding method, antenna guiding device and antenna tracking system |
| CN116191050B (en) * | 2023-04-27 | 2023-09-29 | 贵州师范大学 | Parabolic antenna control system and control method based on motion control card |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103217596A (en) * | 2013-03-06 | 2013-07-24 | 北京空间飞行器总体设计部 | Ground verification method of performance of double-circle polarized multiplexed satellite-borne data transmission antenna |
| CN103592533A (en) * | 2013-10-23 | 2014-02-19 | 航天东方红卫星有限公司 | Data transmission antenna whole-satellite testing method based on minisatellite information system |
| CN104332707A (en) * | 2014-10-27 | 2015-02-04 | 西安空间无线电技术研究所 | Method for tracking ground station through low earth orbit space-borne antenna |
| CN106647704A (en) * | 2016-12-19 | 2017-05-10 | 北京空间飞行器总体设计部 | Method for determining tracking precision of GEO orbital data transmission antenna |
-
2017
- 2017-07-24 CN CN201710607688.3A patent/CN107515410B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103217596A (en) * | 2013-03-06 | 2013-07-24 | 北京空间飞行器总体设计部 | Ground verification method of performance of double-circle polarized multiplexed satellite-borne data transmission antenna |
| CN103592533A (en) * | 2013-10-23 | 2014-02-19 | 航天东方红卫星有限公司 | Data transmission antenna whole-satellite testing method based on minisatellite information system |
| CN104332707A (en) * | 2014-10-27 | 2015-02-04 | 西安空间无线电技术研究所 | Method for tracking ground station through low earth orbit space-borne antenna |
| CN106647704A (en) * | 2016-12-19 | 2017-05-10 | 北京空间飞行器总体设计部 | Method for determining tracking precision of GEO orbital data transmission antenna |
Non-Patent Citations (1)
| Title |
|---|
| 空间惯性定向姿态卫星数传链路设计;熊蔚明 等;《空间科学学报》;20140430;第34卷(第4期);483-488 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107515410A (en) | 2017-12-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107515410B (en) | A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method | |
| CN105184002B (en) | A kind of several simulating analysis for passing antenna pointing angle | |
| CN104332707B (en) | Method for tracking ground station through low earth orbit space-borne antenna | |
| CN111427002B (en) | Azimuth angle calculation method for ground measurement and control antenna pointing satellite | |
| CN107300700B (en) | Agile synthetic aperture radar satellite bunching mode attitude maneuver demand calculation method | |
| CN104236546A (en) | Satellite starlight refraction navigation error determination and compensation method | |
| CN105160125A (en) | Simulation analysis method for star sensor quaternion | |
| CN108917764A (en) | A kind of Double Satellite only ranging Relative Navigation | |
| CN105115508A (en) | Post data-based rotary guided projectile quick air alignment method | |
| CN113788166B (en) | Differential interception tracking method based on space object track error | |
| CN108511908A (en) | A kind of satellite antenna automatic following control system and method inhibiting function with phase | |
| CN109269504A (en) | A kind of attitude maneuver paths planning method with end-fixity | |
| CN108957509A (en) | A kind of Double Satellite's period relative motion only ranging Relative Navigation analytic method | |
| CN105718660B (en) | The a wide range of Maneuver Ballistic Trajectory three-dimensional envelope calculation method of near space | |
| CN106647704B (en) | A kind of GEO track number passes antenna tracking accuracy and determines method | |
| CN103575298A (en) | Self-regulation-based unscented Kalman filter (UKF) misalignment angle initial-alignment method | |
| CN111427001A (en) | Target positioning method suitable for pointing satellite by ground survey station antenna | |
| CN111427004A (en) | Coordinate conversion method suitable for pointing of ground survey station antenna to satellite | |
| CN105825058B (en) | Supersparsity radar data perturbation compensation initial orbit computing method | |
| CN105045298B (en) | A kind of antenna for satellite communication in motion tracking and controlling method based on inertial navigation system Measurement delay | |
| CN106299697B (en) | A kind of method of simple and easy automatic control tracking antenna | |
| CN106250684A (en) | Satellite transit time quick calculation method based on the solid coefficient evidence in ground | |
| CN114132531B (en) | Low-orbit space target orbit correction method and device and electronic equipment | |
| CN110968910A (en) | Double-sight orthogonal laser radar satellite attitude design method and control system | |
| CN110231619A (en) | Radar handover moment forecasting procedure and device based on Encke method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |