CN1959430A - Precision orbit determination system and implementing method for satellites in middle and low orbits - Google Patents
Precision orbit determination system and implementing method for satellites in middle and low orbits Download PDFInfo
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- CN1959430A CN1959430A CNA2006101187364A CN200610118736A CN1959430A CN 1959430 A CN1959430 A CN 1959430A CN A2006101187364 A CNA2006101187364 A CN A2006101187364A CN 200610118736 A CN200610118736 A CN 200610118736A CN 1959430 A CN1959430 A CN 1959430A
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Abstract
A method for realizing precise orbit determination of low-medium orbit satellite utilizes Galileo positioning system, satellite laser distance measurement technique and integrated precise orbit determination new means to optimize space-ground orbit determination system for realizing precise orbit determination of low-medium orbit satellite equipped with laser reflector.
Description
Technical field:
The present invention relates to a kind of system and method that carries laser mirror medium and low earth orbit satellites precise orbit determination,
Specifically, be a kind of by Galileo positioning system, satellite laser ranging (SLR) and Galileo receiver development technology, the novel system of the medium and low earth orbit satellites high precision orbit determination of building up is a kind of new method of effective solution satellite precise orbit determination.
Background technology:
The high precision track is the basis that satellite is effectively controlled.The fast development of China's aerospace industry is determined, is forecast and control computational accuracy and have higher requirement satellite orbit.Make full use of satellite resource and carry out scientific research, the orbit determination accuracy of low-orbit satellite at first must improving, require its radially orbit determination accuracy reach 10cm, low-orbit satellite high precision orbit determination requirement during traditional orbit determination method then is difficult to satisfy must be sought more reliable, more accurate new orbit determination method.
The method of Satellite Orbit Determination technology has a lot, and traditional Satellite Orbit Determination adopts mostly that satellite laser ranging (SLR) (SLR), precise distance measurement are tested the speed (PRARE), Doppler's orbit determination and radiolocation (DORIS) etc.The geodetic satellite (GEOS) lower to track, owing to be subjected to the influence of earth gravitational field bigger, atmosphere power-assisted serious interference, the satellite orbit ratio of precision that adopts traditional orbit determination method to obtain is lower.Along with the appearance of GPS observation technology, make and utilize spaceborne GPS observation technology to carry out the effective means that satellite orbit determines to become satellite precise orbit determination.
The Galileo of European Union estimates operation after 2008, and China mainly adds ally, will enjoy all services such as hi-Fix navigation.Galileo system self, orbital position than GPS height, orbital plane lack, the time signal precision reached for 100 nanoseconds, this just seems and have more advantage on it is used.Therefore, the issue of Galileo system is to improve the opportune moment of utilizing the GPS observation technology.To satellite precise orbit determination, its degree of stability, accuracy and security are better on the basis of using laser ranging technique.
The basic functional principle of laser distance measuring system is: the distance that light is passed by during obtaining by the mistiming of measuring emission laser and reception return laser beam, and then obtain distance value.Satellite laser ranging (SLR) technology (SLR) technology is subjected to the restriction of distribution of land station own and observation time, though do not have the advantage of time and spatial resolution aspect, owing to its precision height, determines the good reliability of satellite position.Therefore, it is a Satellite Orbit Determination, particularly a kind of very important techniques means of satellite transit initial stage orbit determination.SLR single distance accuracy has reached inferior centimeter order, to (millimeter level) the laser ranging development of the 4th generation.It has become one of main supplementary means of satellite precise location observation, also is the highest a kind of of single-point sampling precision in the present various location observation means.
Summary of the invention:
The orbit determination accuracy that the objective of the invention is to overcome the deficiency of existing realization technology and improve medium and low earth orbit satellites.Carrying installation Galileo system receiver on the medium and low earth orbit satellites of laser mirror, receive Doppler shift, pseudorange and carrier phase from the radio signal of Galileo satellites transmits, carry out the first orbit determination of satellite.Simultaneously, satellite laser ranger and Galileo system receiver are installed, are adopted satellite laser ranging (SLR) technology and Galileo system ground location technology to come medium and low earth orbit satellites is calibrated and the secondary precision positioning at ground test point.
The research basis that the present invention communicates by letter between will development, laser ranging technique and star in conjunction with the location technology of Galileo system, Galileo receiver will utilize the Galileo system to realize the medium and low earth orbit satellites precise orbit determination, strive that orbit determination accuracy is stabilized in centimetre-sized.
The method of utilizing the Galileo system to carry out the medium and low earth orbit satellites precise orbit determination can be divided into: (1) geometric method, Doppler, pseudorange and the carrier phase observation data of utilizing spaceborne Galileo system receiver to be received exactly position calculating, thereby provide the position (being the position of corresponding medium and low earth orbit satellites) of receiver.The track that obtains for the first time is one group of discrete some position, and continuous track must provide by approximating method.It is not stress to learn the influence of model error that geometric method orbit determination has very big characteristics, is not subjected to the influence of atmospherical drag model error especially concerning low orbit satellite, and the centering low-orbit satellite has more advantage.The principal element that influences the geometric method orbit measuring precision is the precision of pseudorange observed reading, the formation of Galileo system satellite constellation and continuity, the stability of Galileo system satellite-signal, and the Galileo system has than gps system more performance in these areas.(2) dynamic method, it promptly is traditional orbit determination method, can utilize position detection, pseudorange observation and phase observations and the corresponding observation model of spaceborne Galileo system, provide a kind of measurement equation that other observation method provides that is different from, carry out precise orbit determination.(3) how much dynamic methods are a kind of orbit determination methods that geometric method and dynamic method are combined, and that to be exactly satellite position vector that geometric method is obtained carry out track as observed quantity to the simplest a kind of mode is definite.This method is incorporated into geological information in the mechanical model by increasing process noise, and makes the track deterministic process change between the geometric method in dynamic method by parameter regulation.
The satellite laser ranging (SLR) data processing relates to position and the propagation of laser in atmosphere in the space of the state (position and speed), research station of satellite.The purpose of satellite laser ranging (SLR) data processing is the information of extract being concerned about from the range data of observation, as the exact state (precise orbit determination) of satellite, influence parameter in the mechanical model of satellite motion, survey station the exact position, influence the earth rotation parameter (ERP) of survey station location expression etc.
After must recognizing that a satellite is entered the orbit, must grasp the quantity of state of this satellite all the time in order to follow the tracks of and use this satellite.At first, utilize a large amount of high-precision observational datas to determine a certain moment track amount (precise orbit determination).Secondly, be that the high precision numerical integration that initial value carries out the equation of motion obtains next orbit theory value constantly with fixed track amount.The 3rd, obtain accurate observational data with observing after the accurate forecast of orbit theory value do.There has been new observational data just can repeat first step work and determined corresponding track constantly, gone down, just can grasp the track condition of this satellite, reached precise orbit determination with this.
Innovative point of the present invention:
(1) location technology that adopts high precision Galileo system as in positioning reference between the star of low-orbit satellite precise orbit determination.
(2), the integrated measurement technology in the empty world is carried out seamless connection with SLR technology and Galileo system in combination.
(3) the orbit determination theory with spaceborne Doppler's orbit determination positioning system (DORIS) extends to the medium and low earth orbit satellites precise orbit determination that the present invention proposes, and carries out calibration of ground test point and secondary precision positioning on the basis of first location.
(4) propose on middle low-orbit satellite, laser mirror to be installed, will help laser accurate orbit determination Study on Technology and application.As for the Laser emission mirror is installed on medium and low earth orbit satellites, the realization of this technical requirement can be with reference to the proper star of China's " two generations of the Big Dipper " navigational system.
Technique effect of the present invention:
1. utilize the present invention that the orbit determination accuracy of medium and low earth orbit satellites is stabilized in centimetre-sized, be tending towards the millimeter level.
2. the system layout of the inventive method is simple, and the ground test number of spots reduces to 2, can compatible with GPS system and GLONASS system, can realize the hi-Fix in ground and space.
3. because the first bearing accuracy of Galileo system just can be controlled in decimeter grade, in can shorten observation cycle aspect the Satellite Orbit Determination research of low rail, effectively improved the real-time and the degree of stability of satnav.
Description of drawings:
Fig. 1 is the structural representation of precise orbit determination of the present invention system.
Fig. 2 is the realization block diagram of precise orbit determination method of the present invention.
Embodiment:
See also Fig. 1 earlier, Fig. 1 is the structural representation of precise orbit determination of the present invention system.
Medium and low earth orbit satellites precise orbit determination system based on Galileo positioning system and satellite laser ranging (SLR) comprises satellite laser ranger A (4) and Galileo receiver A (7), satellite laser ranger B (5) and the Galileo receiver B (8) thereof of the Galileo system (only having enumerated satellite A (1) and satellite B (2) wherein among Fig. 1) of operation, the medium and low earth orbit satellites (3) that carries laser mirror and spaceborne Galileo receiver (6) thereof, ground test point.Wherein, it may be noted that: European Galileo plan is middle altitude circle track (MEO) scheme, and this system will be made up of 30 middle altitude circle orbiters and 2 ground control centres, and wherein 27 satellites are the work satellite, and 3 is candidate.Satellite altitude is 24126 kilometers, and being positioned at 3 inclination angles is the orbit plane of 56 degree.Estimating that Galileo system built up in 2008, will be 1 meter location navigation service for European highway, railway, aerial and sea transport, the common defence in Europe or even hiker provide precision securely.
The course of work of system is as follows:
(1) select satellite A of Galileo system (1) and B (2) can realize that bearing accuracy is a sub-meter grade to the location of medium and low earth orbit satellites (3), satellite laser ranger A (4) and B (5) arbitrarily.Wherein, ground test point satellite laser ranger A (4) is to rely on the Galileo receiver A (7) of its installation and B (8) to realize with the location of B (5); The tracks positioned of medium and low earth orbit satellites is to rely on its spaceborne Galileo receiver (6) to realize.
(2) at the satellite laser ranger A (4) of ground test point and B (5) by the laser mirror of emission laser to the satellite (3), thereby realization to the orbit determination of medium and low earth orbit satellites (3), and the coordinate of the land station that refines.
In conjunction with the Fig. 1 and the described course of work thereof, Fig. 2 is the realization block diagram of precise orbit determination method of the present invention.
In sum, precise orbit determination method of the present invention can be summarized as follows:
(1) utilize the Galileo system carry out in the satnav of low rail, obtain required geometric parameter and kinetic parameter;
(2) utilize the Laser emission mirror emission laser of satellite laser ranger, thereby carry out the high precision observation of satellite, obtain required geometric parameter medium and low earth orbit satellites;
(3) integrating step (1) and step (2) are carried out parametric calibration, carry out track and calculate and error correction;
(4) utilize the result of step (3), carry out geometry dynamic method algorithm research; In the process of data processing, adopt difference, Kalman Filtering Model, improve the orbit determination accuracy of medium and low earth orbit satellites.
Compared with the prior art, the present invention has outstanding novelty and significant hi-tech assemblage characteristic.Owing to adopted method based on Galileo high-accuracy position system and the combination of satellite laser ranging (SLR) technology, make the orbit determination accuracy of whole medium and low earth orbit satellites be stabilized in centimetre-sized, be tending towards the millimeter level.By the use of this system, significantly reduced the quantity and the dependence that has reduced the data processing at ground observing and controlling center of ground test point.Simultaneously, eliminate the subjective error that the classic method eye-observation brings, cooperated the use of laser range finder, greatly improved the precision of optical correction, shortened the time of optical correction.Has originality and the high-precision stability of orbit determination in the precise orbit determination field of medium and low earth orbit satellites.
Claims (3)
1, a kind of precise orbit determination system of medium and low earth orbit satellites, system is based on Galileo positioning system and satellite laser ranging (SLR), comprise will operation the satellite A of Galileo system (1) and satellite B (2), one carry the medium and low earth orbit satellites (3) and the spaceborne Galileo receiver (6) thereof of laser mirror, the satellite laser ranger A (4) that is positioned at two test points in ground and Galileo receiver A (7) thereof and satellite laser ranger B (5) and Galileo receiver B (8) thereof; This receiver (6) receives from Doppler shift, pseudorange and the carrier phase of the radio signal of Galileo satellites transmits satellite (3) is carried out first orbit determination; And satellite (3) is calibrated and the secondary precision positioning by satellite laser ranger A (4), B (5) and receiver A (7), B (8).
2, according to the precise orbit determination system of the described medium and low earth orbit satellites of claim 1, it is characterized in that: 1. adopt high precision Galileo positioning system as in positioning reference between the star of low-orbit satellite (3) precise orbit determination; 2. with satellite laser ranging (SLR) (SLR) technology and Galileo system in combination, empty world integrated technique is carried out seamless connection; 3. the orbit determination of spaceborne Doppler's orbit determination positioning system is extended to the precise orbit determination of described medium and low earth orbit satellites, and on the basis of first location, carry out calibration of ground test point and secondary precision positioning.
3, a kind of basic skills that carries laser mirror medium and low earth orbit satellites precise orbit determination comprises step:
(1) utilize the Galileo system carry out in the satnav of low rail, obtain required geometric parameter and kinetic parameter;
(2) utilize the laser mirror reflector laser of satellite laser ranger, thereby carry out the high precision observation of satellite, obtain required geometric parameter medium and low earth orbit satellites;
(3) integrating step (1) and step (2) are carried out parametric calibration, carry out track and calculate and error correction;
(4) utilize the result of step (3), carry out geometry dynamic method algorithm research; In the process of data processing, adopt difference, Kalman Filtering Model, improve the orbit determination accuracy of medium and low earth orbit satellites.
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Cited By (13)
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|---|---|---|---|---|
| CN101881820A (en) * | 2010-07-09 | 2010-11-10 | 中国科学院测量与地球物理研究所 | Mirror surface projection method for precisely determining orbit of geostationary orbit satellite |
| CN103345145A (en) * | 2013-05-27 | 2013-10-09 | 北京空间飞行器总体设计部 | Method for utilizing lasers to conduct satellite borne clock measurement |
| CN104657795A (en) * | 2015-03-16 | 2015-05-27 | 中国人民解放军空军装备研究院雷达与电子对抗研究所 | To-be-observed task determination method and device of multi-satellite earth synergetic observation |
| CN106646564A (en) * | 2016-10-31 | 2017-05-10 | 电子科技大学 | Navigation enhancing method based on low track satellite |
| CN108061908A (en) * | 2017-12-11 | 2018-05-22 | 山东科技大学 | SLR station three-dimensional coordinate geometry calculation methods based on the spaceborne GNSS technologies of low orbit satellite |
| CN109061674A (en) * | 2018-06-28 | 2018-12-21 | 上海卫星工程研究所 | The system and method that dipper system continuous service is monitored using Constellation of Low Earth Orbit Satellites |
| CN109283552A (en) * | 2018-09-14 | 2019-01-29 | 广州磐钴智能科技有限公司 | A kind of satellite high-precision positioning quick environment monitoring method and equipment |
| CN110031881A (en) * | 2019-05-06 | 2019-07-19 | 中国人民解放军61540部队 | The method of laser ranging auxiliary Static Precise Point Positioning between high precision star |
| CN110058287A (en) * | 2019-05-16 | 2019-07-26 | 北京合众思壮科技股份有限公司 | A kind of Orbit determination for LEOs method, apparatus and system |
| CN110118978A (en) * | 2019-04-15 | 2019-08-13 | 中国人民解放军军事科学院国防科技创新研究院 | Navigation jamproof system and navigation anti-interference method based on low orbit satellite |
| CN110285835A (en) * | 2019-07-19 | 2019-09-27 | 上海微小卫星工程中心 | A kind of satellite system of Precise Orbit calibration |
| US20210033705A1 (en) * | 2018-04-03 | 2021-02-04 | Arianegroup Sas | Method and system for emitting and receiving laser pulses |
| CN114509790A (en) * | 2022-02-17 | 2022-05-17 | 北京国电高科科技有限公司 | Positioning method and positioning system based on low-orbit satellite constellation |
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- 2006-11-24 CN CNA2006101187364A patent/CN1959430A/en active Pending
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101881820A (en) * | 2010-07-09 | 2010-11-10 | 中国科学院测量与地球物理研究所 | Mirror surface projection method for precisely determining orbit of geostationary orbit satellite |
| CN103345145A (en) * | 2013-05-27 | 2013-10-09 | 北京空间飞行器总体设计部 | Method for utilizing lasers to conduct satellite borne clock measurement |
| CN103345145B (en) * | 2013-05-27 | 2016-03-30 | 北京空间飞行器总体设计部 | A kind of method utilizing laser to carry out spaceborne clock measurement |
| CN104657795A (en) * | 2015-03-16 | 2015-05-27 | 中国人民解放军空军装备研究院雷达与电子对抗研究所 | To-be-observed task determination method and device of multi-satellite earth synergetic observation |
| CN106646564B (en) * | 2016-10-31 | 2019-10-29 | 电子科技大学 | One kind being based on low orbit satellite enhanced navigation method |
| CN106646564A (en) * | 2016-10-31 | 2017-05-10 | 电子科技大学 | Navigation enhancing method based on low track satellite |
| CN108061908A (en) * | 2017-12-11 | 2018-05-22 | 山东科技大学 | SLR station three-dimensional coordinate geometry calculation methods based on the spaceborne GNSS technologies of low orbit satellite |
| CN108061908B (en) * | 2017-12-11 | 2020-01-17 | 山东科技大学 | SLR station three-dimensional coordinate geometric resolving method based on low-earth-orbit satellite-borne GNSS technology |
| US20210033705A1 (en) * | 2018-04-03 | 2021-02-04 | Arianegroup Sas | Method and system for emitting and receiving laser pulses |
| CN109061674A (en) * | 2018-06-28 | 2018-12-21 | 上海卫星工程研究所 | The system and method that dipper system continuous service is monitored using Constellation of Low Earth Orbit Satellites |
| CN109061674B (en) * | 2018-06-28 | 2020-09-15 | 上海卫星工程研究所 | System and method for continuously monitoring operation of Beidou system by using low-earth-orbit satellite constellation |
| CN109283552A (en) * | 2018-09-14 | 2019-01-29 | 广州磐钴智能科技有限公司 | A kind of satellite high-precision positioning quick environment monitoring method and equipment |
| CN110118978B (en) * | 2019-04-15 | 2020-05-19 | 中国人民解放军军事科学院国防科技创新研究院 | Navigation anti-interference system and navigation anti-interference method based on low-earth-orbit satellite |
| CN110118978A (en) * | 2019-04-15 | 2019-08-13 | 中国人民解放军军事科学院国防科技创新研究院 | Navigation jamproof system and navigation anti-interference method based on low orbit satellite |
| CN110031881A (en) * | 2019-05-06 | 2019-07-19 | 中国人民解放军61540部队 | The method of laser ranging auxiliary Static Precise Point Positioning between high precision star |
| CN110058287A (en) * | 2019-05-16 | 2019-07-26 | 北京合众思壮科技股份有限公司 | A kind of Orbit determination for LEOs method, apparatus and system |
| CN110285835A (en) * | 2019-07-19 | 2019-09-27 | 上海微小卫星工程中心 | A kind of satellite system of Precise Orbit calibration |
| CN114509790A (en) * | 2022-02-17 | 2022-05-17 | 北京国电高科科技有限公司 | Positioning method and positioning system based on low-orbit satellite constellation |
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