CN106647704A - Method for determining tracking precision of GEO orbital data transmission antenna - Google Patents
Method for determining tracking precision of GEO orbital data transmission antenna Download PDFInfo
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- CN106647704A CN106647704A CN201611179342.XA CN201611179342A CN106647704A CN 106647704 A CN106647704 A CN 106647704A CN 201611179342 A CN201611179342 A CN 201611179342A CN 106647704 A CN106647704 A CN 106647704A
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- 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
Abstract
The invention discloses a method for determining the tracking precision of a GEO orbital data transmission antenna. The method carries out the research of the impact on the tracking precision of the antenna from all links (target angle determining precision, servo control precision and antenna pointing precision) according to the tracking control principle of the GEO orbital data transmission antenna, so an antenna tracking precision determining method is built. The method solves a problem that the tracking precision of the antenna cannot be precisely determined in the prior art, and can be used for the analysis, modeling and verification of the tracking control precision of the GEO orbital data transmission antenna.
Description
Technical field
The present invention relates to a kind of GEO track numbers pass antenna tracking accuracy determines method, can be used for GEO orbiters antenna with
Analysis, modeling and the checking work of track control accuracy.
Background technology
The GEO orbiters of " in-orbit frequent low-angle motor-driven imaging pattern ", are guarantor in whole star mobile process to possessing
Card star ground radio frequency transmission link does not interrupt and guarantees that Radio Link surplus meets use requirement, and it is accurate, real that number passes antenna needs
When reversely low-angle is frequently motor-driven tracking earth station location on ground.Antenna pointing error can cause EIRP (etc. in service area
Effect isotropically radiated power) etc. index change, drastically increasing for transmission error rates can be caused when serious.Therefore for high rail long distance
From star, number is transmitted and said, antenna tracking accuracy has very high requirement.
GEO orbiters participate in the part of Antenna pointing control includes Attitude and orbit control system, satellited system and Data transfer system
Multiple devices.When number passes antenna tracking control, the information such as introducing extraneous track, attitude, time are needed to complete antenna rotating machine
Traceback of the structure to earth station, is related to link many.Meanwhile, in addition to analysis, incorporation engineering experience is also needed, to power, hot iso-stress
The error that condition causes rationally is estimated.
Low rail remote sensing satellite imaging is generally push-broom pattern, and satellite does not have frequent low-angle machine in rolling and pitch orientation
It is dynamic；The generally fixed spot beam of high rail telecommunication satellite or zone beam, antenna sensing is constant all the time, is not specifically designed for satellite and exists
Frequently number passes the determination method of Antenna pointing control under low-angle maneuver model.Because GEO rail communications distance is remote, and used
Beam angle it is narrow, traditional sensing control method star ground antenna difficult to realize is accurately aligned, and link margin is difficult to ensure.
The content of the invention
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art, there is provided a kind of GEO track numbers pass antenna with
Track precision determines method, and according to GEO orbiters number antenna tracking control principle is passed, and precision, SERVO CONTROL are determined to target angle
The impacts of each link to antenna tracking accuracy such as precision, antenna pointing accuracy itself are studied, and set up a set of antenna tracking essence
The determination method of degree, can be used for analysis, modeling and the checking work of GEO orbiter antenna tracking control accuracies.
The present invention technical solution be：A kind of GEO track numbers pass antenna tracking accuracy and determine method, including following step
Suddenly：
(1) GEO track numbers are passed into antenna tracking accuracy ETotalIt is divided into target angle and determines error EA, servo control error
EB, antenna error in pointing E itselfC
Wherein：
(2) target angle is determined into error EAIt is divided into orbit error E1, attitude error E2, time error E3, ground station error
E4, control computer algorithm and hardware error E5
Wherein：
(3) by servo control error EBIt is divided into measure error E of servo controller internal rotating transformer6, servo control mechanism
Perform error E7
Wherein：
(4) by antenna error in pointing E itselfCIt is divided into the electrical boresight of antenna and mechanical axis constant value deviation E8, the electrical boresight of antenna with machinery
Axle power thermal deformation deviation E9, aerial mechanical error of zero E10, antenna double-axle rotation mechanism rotation error E11, the traditional thread binding star error in day
E12
In formula：
(5) orbit error E is obtained1, attitude error E2, time error E3, earth station's error E4, control computer algorithm and
Hardware error E5, servo controller internal rotating transformer measure error E6, servo control mechanism perform error E7, the electrical boresight of antenna with
Mechanical axis constant value deviation E8, the electrical boresight of antenna and mechanical axle power thermal deformation deviation E9, aerial mechanical error of zero E10, antenna twin shaft turn
Motivation structure rotation error E11, the traditional thread binding star error E in day12, and then it is calculated GEO track numbers biography antenna tracking accuracy ETotal。
Present invention advantage compared with prior art is：Inventive antenna tracking accuracy determines that method solves GEO rails
Star ground communication distance long-range guided missile in road causes Free propagation loss greatly, and the Ka frequency ranges electromagnetic wave for being used easily is declined by rain and affected, and antenna ripple
Beam width is narrow, and whether star ground antenna accurately greatly affects Radio Link surplus, traditional determination method to be directed on brigadier
The pointing accuracy of such satellite antenna carries out the problem of budget, with preferable use value.
Description of the drawings
Fig. 1 is that number of the present invention passes antenna rotation control principle；
Fig. 2 is that number of the present invention passes antenna tracking error decomposing schematic representation.
Specific embodiment
Overcome the deficiencies in the prior art, there is provided a kind of GEO track numbers pass antenna tracking accuracy and determine method, according to GEO
Orbiter number passes antenna tracking control principle, and precision, SERVO CONTROL precision, antenna pointing accuracy itself etc. are determined to target angle
Impact of each link to antenna tracking accuracy is studied, and sets up the determination method of a set of antenna tracking accuracy, can be used for GEO rails
Analysis, modeling and the checking work of road satellite antenna tracing control precision.The inventive method is carried out in detail below in conjunction with the accompanying drawings
Illustrate, the inventive method comprises the steps：
(1) GEO orbiters number biography antenna rotation control flow is：House keeping computer sends instruction and makes to control computer
Can be from host computer antenna corner；The attitude of satellite data that control computer is obtained according to satellite attitude measurement equipment, calculate antenna
Rotational angle, control unit is passed by house keeping computer Jing 1553B bus broadcasts to number；Number passes control units according to receiving
Rotational angle information controls servo controller, by the motion of double-axle rotation mechanism, completes logarithm and passes antenna sensing earth station
Control.Idiographic flow is as shown in Figure 1.Control principle is rotated according to antenna, according to information source error, information transmission error and is held
The influence factor of row error analysis tracking accuracy.
(2) information source error and information transmission error have together decided on target angle and have determined error, and performing error includes servo
Control error and antenna error in pointing itself.Logarithm passes antenna tracking error influence factor and is modeled analysis, is decomposed into target
Angle determines error, servo control error and antenna error in pointing itself, and modeling situation refers to accompanying drawing 2.The every source of error of analysis,
Contribution margin of the estimation to the final tracking accuracy of antenna, according to antenna the correlation between control information stream and each influence factor is rotated,
Calculate the in-orbit tracking accuracy of satellite data transmission antenna.Refer to formula (1) (2) (3) (4).
In formula：ETotalThe total tracking error of antenna, E are passed for numberADetermine error, E for target angleBFor servo control error, ECFor
Antenna error in pointing itself；
In formula：E1For orbit error, E2For attitude error, E3For time error, E4For ground station error (position and height
Journey), E5For control computer algorithm and hardware error；
In formula：E6For the measure error of servo controller internal rotating transformer, E7Error is performed for servo control mechanism；
In formula：E8For the electrical boresight of antenna and mechanical axis deviation (constant value part, ground can measure), E9For the electrical boresight of antenna and machinery
Axle deviation (power thermal deformation), E10For the aerial mechanical error of zero, E11For antenna double-axle rotation mechanism rotation error, E12For antenna
Dress star error.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (1)
1. a kind of GEO track numbers biography antenna tracking accuracy determines method, it is characterised in that comprise the steps：
(1) GEO track numbers are passed into antenna tracking accuracy ETotalIt is divided into target angle and determines error EA, servo control error EB, antenna
Error in pointing E itselfC
Wherein：
(2) target angle is determined into error EAIt is divided into orbit error E1, attitude error E2, time error E3, earth station's error E4, control
Computerized algorithm processed and hardware error E5
Wherein：
(3) by servo control error EBIt is divided into measure error E of servo controller internal rotating transformer6, servo control mechanism perform
Error E7
Wherein：
(4) by antenna error in pointing E itselfCIt is divided into the electrical boresight of antenna and mechanical axis constant value deviation E8, the electrical boresight of antenna and mechanical axle power
Thermal deformation deviation E9, aerial mechanical error of zero E10, antenna double-axle rotation mechanism rotation error E11, the traditional thread binding star error E in day12
In formula：
(5) orbit error E is obtained1, attitude error E2, time error E3, earth station's error E4, control computer algorithm and hardware misses
Difference E5, servo controller internal rotating transformer measure error E6, servo control mechanism perform error E7, the electrical boresight of antenna and mechanical axis
Constant value deviation E8, the electrical boresight of antenna and mechanical axle power thermal deformation deviation E9, aerial mechanical error of zero E10, antenna double-axle rotation mechanism
Rotation error E11, the traditional thread binding star error E in day12, and then it is calculated GEO track numbers biography antenna tracking accuracy ETotal。
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| CN201611179342.XA CN106647704B (en) | 2016-12-19 | 2016-12-19 | A kind of GEO track number passes antenna tracking accuracy and determines method |
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| CN201611179342.XA CN106647704B (en) | 2016-12-19 | 2016-12-19 | A kind of GEO track number passes antenna tracking accuracy and determines method |
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| CN106647704B CN106647704B (en) | 2019-11-12 |
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Cited By (5)
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| CN107515410A (en) * | 2017-07-24 | 2017-12-26 | 北京控制工程研究所 | A kind of spacecraft tests checking system and method with Shuo Chuan antenna trackings earth station |
| CN111399525A (en) * | 2020-02-26 | 2020-07-10 | 上海航天控制技术研究所 | Mars detector ground antenna control method considering both accurate pointing and position safety |
| CN113156225A (en) * | 2021-04-25 | 2021-07-23 | 上海航天测控通信研究所 | Deep space high-gain antenna on-orbit pointing calibration method |
| CN113946532A (en) * | 2021-08-26 | 2022-01-18 | 西安空间无线电技术研究所 | Satellite-borne 1553B control bus failure protection method |
| CN113946532B (en) * | 2021-08-26 | 2024-05-03 | 西安空间无线电技术研究所 | Satellite-borne 1553B control bus failure protection method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107515410A (en) * | 2017-07-24 | 2017-12-26 | 北京控制工程研究所 | A kind of spacecraft tests checking system and method with Shuo Chuan antenna trackings earth station |
| CN107515410B (en) * | 2017-07-24 | 2019-08-09 | 北京控制工程研究所 | A kind of spacecraft Shuo Chuan antenna tracking earth station test verifying system and method |
| CN111399525A (en) * | 2020-02-26 | 2020-07-10 | 上海航天控制技术研究所 | Mars detector ground antenna control method considering both accurate pointing and position safety |
| CN111399525B (en) * | 2020-02-26 | 2023-05-12 | 上海航天控制技术研究所 | Mars detector ground antenna control method considering both precise pointing and position safety |
| CN113156225A (en) * | 2021-04-25 | 2021-07-23 | 上海航天测控通信研究所 | Deep space high-gain antenna on-orbit pointing calibration method |
| CN113156225B (en) * | 2021-04-25 | 2022-05-27 | 上海航天测控通信研究所 | Deep space high-gain antenna on-orbit pointing calibration method |
| CN113946532A (en) * | 2021-08-26 | 2022-01-18 | 西安空间无线电技术研究所 | Satellite-borne 1553B control bus failure protection method |
| CN113946532B (en) * | 2021-08-26 | 2024-05-03 | 西安空间无线电技术研究所 | Satellite-borne 1553B control bus failure protection method |
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Inventor after: Liu Ning Inventor after: Liu Yunhe Inventor after: Wang Lili Inventor after: Yu Dengyun Inventor after: Shi Lijuan Inventor after: Ren Xiaohang Inventor after: Yu Longjiang Inventor after: Liu Fengjing Inventor after: Liu Xingchen Inventor after: Wang Aiming Inventor after: Kong Xianghao Inventor before: Liu Ning Inventor before: Wang Lili Inventor before: Shi Lijuan Inventor before: Ren Xiaohang Inventor before: Yu Longjiang Inventor before: Liu Fengjing Inventor before: Liu Xingchen Inventor before: Wang Aiming Inventor before: Kong Xianghao Inventor before: Liu Yunhe |
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