CN102636818B - Star follows the tracks of compound formation earth gravity field measuring system and method thereof - Google Patents
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Abstract
The invention provides and a kind ofly utilize the composition of fleet system in two or more star to follow the tracks of compound to form into columns and carry out system and the method thereof of gravity field measurement.This system, comprises fleet system in two or more, and wherein each described interior fleet system includes interior satellite and outer satellite platform; Described outer satellite platform comprises outer satellite body and is arranged on the subsystem on described outer satellite body; Be provided with cavity in described outer satellite body, described interior satellite is placed in described cavity.During described interior fleet system operation on orbit, the described interior satellite in two described interior fleet system all runs along pure Attractive Orbit; Utilize the relative status measurement data of described outer precision orbit determination data and described interior satellite and described outer satellite, determine the pure Attractive Orbit of described interior satellite; Measure the interstellar distance rate of change between two described interior satellites, carry out inverting with this and obtain middle high-order earth gravity field.
Description
Technical field
The present invention relates to Space Vehicle System technology and Geodetic Technique field, particularly relate to a kind of star and follow the tracks of compound formation earth gravity field measuring system and method thereof.
Background technology
Earth gravity field is the basic physical field of the earth, affects the physical event of the earth itself and proximity space thereof, and therefore terrestrial gravitation field measurement and research are always geodesic core and hot issue.According to the difference measuring carrier, terrestrial gravitation field measurement can be divided into surface gravity survey, marine gravimetric survey, airborne gravimetry and satellite gravity survey.Wherein, satellite gravity survey has round-the-clock, Global coverage, not by technical advantages such as geographical environment affect, is the most effective means obtaining global gravity measurement data.According to the difference of observation data, gravity field measurement of satellites can be divided into orbit perturbation, star to follow the tracks of and gravity gradient three kinds of metering systems.Three kinds of metering systems all can obtain the gravity field information of full spectral coverage, but they are different to the responsive frequency range of gravitation position, and orbit perturbation, star are followed the tracks of and gradiometry is easy to responsive low order, middle high-order and high-order terrestrial gravitation field information respectively.Due to the existence of external interference and measuring error, Gravity Satellite is difficult on full spectral coverage, obtain the consistent gravitation position information of precision simultaneously, and their actual observation abilities in corresponding responsive frequency range are determined by satellite load measuring accuracy.Visible, improving load measurement level is the key realizing high precision gravity field measurement of satellites.
Accelerometer is one of crucial load determining gravity field measuring accuracy, for measuring the non-gravitation interference that verification quality is subject to, Gravity Satellite as external in CHAMP, GRACE, GRACEFollow-on etc. all utilizes accelerometer to carry out the accurate measurement of non-gravitation interference.But, accelerometer is a kind of exact instrument of costliness, require very high to satellite manufacturing technology and satellite platform control technology, China does not also possess the high-precision accelerometer that can be used for satellite gravity survey at present, and this seriously governs the Project Realization of China's Gravity Satellite system schema.
Summary of the invention
For overcoming the above problems, the invention provides and a kind ofly utilize the composition of fleet system in two or more star to follow the tracks of compound to form into columns and carry out system and the method thereof of gravity field measurement.This system and method have employed star and follows the tracks of gravity field measuring principle, is measured and precision orbit determination, realize the high-acruracy survey of middle and high terrace gravity field by interstellar distance.
The object of the present invention is to provide a kind of star to follow the tracks of compound formation earth gravity field measuring system and method thereof, thus solve problems of the prior art.
To achieve these goals, the technical solution used in the present invention is as follows:
A kind of star follows the tracks of compound formation earth gravity field measuring system, and comprise fleet system in two or more, wherein each described interior fleet system includes interior satellite and outer satellite platform; Described outer satellite platform comprises outer satellite body and is arranged on the subsystem on described outer satellite body; Be provided with cavity in described outer satellite body, described interior satellite is placed in described cavity.
Preferably, the subsystem be arranged on described outer satellite body comprises: intersatellite ranging system, outer precision orbit determination system, inside and outside satellite relative status measuring system, interior satellite system latch mechanism, outer measuring system of satellite attitude, outer satellite attitude control system, micromass culture system, data storage cell and data transmission unit.
Preferably,
Described intersatellite ranging system, comprises differential laser interfeerometry ranging instrument between high precision star; Described intersatellite ranging system is used for the interstellar distance rate of change between two adjacent described interior fleet system of precision measurement;
Described outer precision orbit determination system, comprises spaceborne double frequency conventional differential GPS receiver and laser retroreflective array; Described outer precision orbit determination system is used for the accurate orbit determining described outer satellite;
Described inside and outside satellite relative status measuring system, comprises interior satellite normal temperature infrared imaging detector, adopts IR Passive measuring principle; Described inside and outside satellite relative status measuring system is for measuring relative position and the relative velocity of described interior satellite and described outer satellite;
Described interior satellite system latch mechanism, for the locking of described interior satellite and release;
Described outer measuring system of satellite attitude, comprises sun sensor, star sensor and magnetometer; Described outer measuring system of satellite attitude, determines for the described outer attitude of satellite;
Described outer satellite attitude control system, comprises flywheel and magnetic torquer; Described flywheel is used for described outer satellite three-axis attitude stabilization; Described magnetic torquer is used for the unloading of described flywheel;
Described micromass culture system, can provide milli ox magnitude thrust; Described micromass culture system, controls for described outer satellite orbit; Relative status also for described interior satellite and described outer satellite controls;
Described data storage cell, the data of storage comprise in following data one or more or all: the relative status data of interstellar distance rate of change data, described interior satellite and described outer satellite between the orbit determination data of described outer satellite, described adjacent two interior fleet system;
Described data transmission unit, transmits earthward for the data stored by described data storage cell.
Preferably, the cavity in described outer satellite body is spherical cavity, and described cavity diameter is 10 ~ 100 times of described interior satellite diameter.
Preferably, described interior satellite is the spherical verification quality that nominal position is positioned at described chamber central; The plation that described interior satellite is 66: 34 by volume ratio is formed.
Preferably, described interior fleet system adopts the sun synchronization track in morning and evening of 200 ~ 300km height, and described track is near polar orbits, and described orbital eccentricity is 0.001.
Preferably, the interstellar distance between adjacent two described interior fleet system is 50 ~ 150km.
Preferably, the number of the interior fleet system included by described star tracking compound formation earth gravity field measuring system is two.
Apply described star and follow the tracks of the method that compound formation earth gravity field measuring system measures earth gravity field: a during described interior fleet system operation on orbit, the described interior satellite in two described interior fleet system all runs along pure Attractive Orbit; Then, utilize the relative status measurement data of outer precision orbit determination data and described interior satellite and described outer satellite, determine the pure Attractive Orbit of described interior satellite; Measure the interstellar distance rate of change between two described interior satellites, carry out inverting with this and obtain middle high-order earth gravity field.
Preferably, the method for described measurement earth gravity field specifically comprises the steps:
Step 1: the sun synchronization track in morning and evening two described interior fleet system being sent into simultaneously 200 ~ 300km height, follow the tracks of along satellite flight direction composition star and form into columns, interstellar distance is 50 ~ 150km;
Step 2: open the described interior satellite system latch mechanism in two described interior fleet system, is discharged in the cavity of described outer satellite by described interior satellite;
Step 3: for each described interior fleet system, relative position and the relative velocity of described interior satellite and described outer satellite is obtained by described inside and outside satellite relative status measuring system measurement, then outer satellite orbit described in described micromass culture Systematical control is utilized, adjust the relative position of described interior satellite and described outer satellite, the barycenter of described interior satellite and described outer satellite is overlapped, and the star formed based on interior formation follows the tracks of compound formation;
Step 4: for each described interior fleet system, utilizes described sun sensor, described star sensor and described magnetometer to realize attitude measurement, and is supplied to described outer satellite attitude control system;
Step 5: utilize described flywheel to realize described outer satellite three-axis attitude stabilization, utilizes described magnetic torquer to realize the unloading of described flywheel;
Step 6: utilize described spaceborne double frequency conventional differential GPS receiver and described laser retroreflective array, orbit determination measures described outer satellite orbit; Utilize differential laser interfeerometry ranging instrument between described high precision star, measure the interstellar distance rate of change between described two interior fleet system;
Step 7: by the interstellar distance rate of change data between the relative status measurement data of described outer Satellite Orbit Determination data, described interior satellite and described outer satellite, described interior fleet system, be saved in described data storage cell, be the gravity field measurement data of this point;
Step 8: repeat step 3 to 7, each point data of continuous coverage, and reach land station by described data transmission unit by under the described gravity field measurement data of each point;
Step 9: after at least completing a Global coverage measurement, reach the described gravity field measurement data of land station under utilizing the process of Earth's gravity field recovery computational tool, inverting obtains earth gravity field model.
The invention has the beneficial effects as follows:
1, star tracking compound formation earth gravity field measuring system provided by the invention and method have effectively achieved the gravity field measurement of middle and high rank under the condition not relying on accelerometer load.
2, the present invention realizes the gravity field measurement of middle and high rank by the interstellar distance rate of change between measurement two interior satellites, and relative to prior art, the present invention realizes simply, precision is high, cost is low, meets middle and high rank gravity field measurement demand simultaneously.
Accompanying drawing explanation
Fig. 1 star follows the tracks of compound formation gravity field measuring system schematic diagram;
Fig. 2 star follows the tracks of compound formation gravity field measuring system schematic diagram;
Fig. 3 star follows the tracks of compound formation Global coverage instrumentation plan;
Fig. 4 star follows the tracks of compound formation sub-satellite track;
Wherein: 1, differential laser interfeerometry ranging instrument between high precision star; 2, magnetometer; 3, solar panel; 4, sun sensor; 5, antenna; 6, interior satellite normal temperature infrared imaging detector; 7, interior satellite system latch mechanism; 8, pneumatic empennage; 9, thruster; 10, service module after outer satellite; 11, outer satellite cavity; 12, service module before outer satellite; 13, star sensor; 21, outer satellite; 22, interior satellite; 24, spaceborne double frequency conventional differential GPS receiver; 25, laser retroreflective array; 26, ground laser ranging station.
Embodiment
The present invention utilizes the star based on interior formation to follow the tracks of compound and forms into columns, and realizes the high-acruracy survey of middle and high terrace gravity field.
Star of the present invention is followed the tracks of compound formation earth gravity field measuring system and is included two interior fleet system, can certainly comprise plural interior fleet system, and wherein each interior fleet system is all formed primarily of interior satellite and outer satellite platform.Outer satellite platform comprises outer satellite body and is arranged on the subsystem on described outer satellite body; Be provided with cavity in described outer satellite body, described interior satellite is placed in described cavity.The subsystem that outer satellite body is installed mainly contains intersatellite ranging system, outer precision orbit determination system, inside and outside satellite relative status measuring system, interior satellite system latch mechanism, outer measuring system of satellite attitude, outer satellite attitude control system, micromass culture system, data storage cell and data transmission unit.Intersatellite ranging system adopts differential laser interfeerometry ranging instrument between high precision star, for the interstellar distance rate of change in precision measurement two between formation.Outer precision orbit determination system is formed primarily of spaceborne double frequency conventional differential GPS receiver and laser retroreflective array, determines outer satellite orbit for precision.Inside and outside satellite relative status measuring system adopts IR Passive measuring principle, for measuring inside and outside satellite relative position and relative velocity.Interior satellite system latch mechanism is used for locking and the release of interior satellite.Outer measuring system of satellite attitude, primarily of sun sensor, star sensor and magnetometer composition, is determined for the outer attitude of satellite.Outer satellite attitude control system is formed primarily of flywheel and magnetic torquer, utilizes flywheel to realize outer satellite three-axis attitude stabilization, utilizes magnetic torquer to realize flywheel unloading.Micromass culture system can provide milli ox magnitude thrust, controls and the control of inside and outside satellite relative status for outer satellite orbit.Data storage cell and transmission unit are used for the gravity field measurement data such as outer Satellite Orbit Determination data, interstellar distance rate of change data, inside and outside satellite relative status to carry out preserving and transmitting earthward.Outer satellite has spherical cavity, and interior satellite is the spherical verification quality that nominal position is positioned at chamber central.In-orbit during normal formation flight, interior satellite along pure Attractive Orbit free flight, controls outer satellite orbit and attitude in real time in cavity, and inside and outside centroid of satellite deviation is kept in allowed limits.
During operation on orbit, interior satellite in two interior fleet system all runs along pure Attractive Orbit, GPS orbit determination, laser retroreflective array orbit determination and the measurement of inside and outside satellite relative status is utilized to determine the pure Attractive Orbit of interior satellite, utilize differential laser interfeerometry ranging instrument between high precision star to measure the interstellar distance rate of change between two interior satellites, carry out high-order earth gravity field in inverting with this.
The method applying star of the present invention tracking compound formation earth gravity field measuring system measurement earth gravity field comprises the steps:
Step 1: the sun synchronization track in morning and evening two interior fleet system being sent into simultaneously 200 ~ 300km height, follow the tracks of along satellite flight direction composition star and form into columns, interstellar distance is 50 ~ 150km;
Step 2: opening in two interior fleet system is latch mechanism, is discharged into by interior satellite in outer satellite cavity;
Step 3: for each interior fleet system, inside and outside satellite relative position and relative velocity is obtained by relative status measuring system, then the outer satellite orbit of micromass culture Systematical control is utilized, adjust inside and outside satellite relative position, both barycenter are overlapped, and the star formed based on interior formation follows the tracks of compound formation;
Step 4: for each interior fleet system, utilizes sun sensor, star sensor and magnetometer to realize attitude measurement, is supplied to outer satellite attitude control system;
Step 5: utilize flywheel to realize outer satellite three-axis attitude stabilization, utilizes magnetic torquer to realize flywheel unloading;
Step 6: utilize GPS orbit determination, the outer satellite orbit of laser retroreflective array orbit determination mensuration, utilize differential laser interfeerometry ranging instrument between high precision star to measure the interstellar distance rate of change between two interior fleet system;
Step 7: outer Satellite Orbit Determination data, inside and outside satellite relative status measurement data, interstellar distance rate of change data are saved in spaceborne data storage cell, are the gravity field measurement data of this point;
Step 8: repeat step 3 ~ 7, each point data of continuous coverage, and reach land station by data transfer unit by under gravity field measurement data;
Step 9: after at least completing a Global coverage measurement, utilize Earth's gravity field recovery computational tool manipulate measurement data, inverting obtains earth gravity field model.
In order to make technical matters solved by the invention, technical scheme and beneficial effect clearly understand, below in conjunction with accompanying drawing, the present invention is further elaborated.Should be appreciated that embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
Accompanying drawing 1 is that star follows the tracks of compound formation gravity field measuring system schematic diagram, and accompanying drawing 2 is that star follows the tracks of compound formation gravity field measuring system schematic diagram.
The star of present embodiment is followed the tracks of compound formation earth gravity field measuring system and is made up of two interior fleet system, and wherein each interior fleet system is formed by outer satellite platform and interior satellite.Outer satellite platform comprises outer satellite body and is arranged on the subsystem on described outer satellite body; Cavity is provided with in described outer satellite body, described interior satellite is placed in described cavity, and the subsystem that outer satellite body is installed comprises intersatellite ranging system, outer precision orbit determination system, inside and outside satellite relative status measuring system, interior satellite system latch mechanism, outer measuring system of satellite attitude, outer satellite attitude control system, micromass culture system, data storage cell, data transmission unit.Outer satellite platform has spherical cavity, and its diameter is 10 ~ 100 times of interior satellite diameter.Interior satellite is the spherical verification quality that nominal position is positioned at chamber central, is made up of volume ratio 66: 34 plation.
Intersatellite ranging system adopts differential laser interfeerometry ranging instrument between high precision star, and for the interstellar distance rate of change in precision measurement two between formation, measuring accuracy reaches 8 ~ 10nm/s.Outer precision orbit determination system is made up of spaceborne double frequency conventional differential GPS receiver and laser retroreflective array, determines outer satellite orbit for precision, and orbit determination accuracy is 5cm.Inside and outside satellite relative status measuring system adopts IR Passive measuring principle, use interior satellite normal temperature infrared imaging detector, two vertically arranged CCD camera measurements are utilized to obtain the direction of interior satellite relative to camera, two camera datas are combined and are solved, inside and outside satellite relative position and relative velocity can be determined, relative position measurement precision is better than 1mm, and relative velocity measuring accuracy is better than 0.1mm/s.Interior satellite system latch mechanism is used for locking and the release of interior satellite.Outer measuring system of satellite attitude is made up of sun sensor, star sensor and magnetometer, determines for the outer attitude of satellite.Outer satellite attitude control system is made up of flywheel and magnetic torquer, utilizes flywheel to realize outer satellite three-axis attitude stabilization, utilizes magnetic torquer to realize flywheel unloading.Micromass culture system can provide mN magnitude thrust, is chosen as the cold air propelling of applicable moonlet application, electric propulsion or laser propulsion device, controls and the closed-loop control of inside and outside satellite relative status for outer satellite orbit.Data storage cell and transmission unit are used for the gravity field measurement data such as outer Satellite Orbit Determination data, interstellar distance rate of change data, inside and outside satellite relative status to preserve, and transmit earthward.
After two interior fleet system are sent into track, opening is that interior satellite discharges by latch mechanism, is measured and propulsion system control by inside and outside satellite relative status, and in realizing, formation star follows the tracks of the initialization of compound formation configuration.Two interior satellites all along pure Attractive Orbit free flight, satellite orbits in two outer satellite tight trackings are corresponding.When there is deviation in inside and outside satellite relative position, utilize relative status measurement data and the outer satellite orbit of micromass culture control system adjustment, inside and outside centroid of satellite deviation is kept in allowed limits, realize the long term maintenance that star follows the tracks of compound formation, meet the collection requirement of gravity field measurement data.
The star that the present invention is based on interior formation follows the tracks of the sun synchronization track in morning and evening of compound formation employing 200 ~ 300km height, and it is also near polar orbits, and orbital eccentricity is 0.001, and interstellar distance is 50 ~ 150km.Because gravity field signal is decayed with the increase of orbit altitude, so orbit altitude should be made under the condition meeting Project Realization low as far as possible.Sun synchronization track in morning and evening ensure that the stability of satellite illumination condition and the normal work of solar panel, near polar orbits ensure that the basic Global coverage of gravity field measurement data, accompanying drawing 3 is that the interior formation star of 250km orbit altitude follows the tracks of compound formation Global coverage instrumentation plan, and accompanying drawing 4 is corresponding sub-satellite tracks.Small eccentricity rate circular orbit makes satellite spatial environment consistent as far as possible, is convenient to satellite and controls, and makes measure data precision consistent as far as possible simultaneously, is conducive to the raising of gravity field inversion accuracy.Interstellar distance is chosen as spatial resolution corresponding to measurement target exponent number, is conducive to the signal to noise ratio (S/N ratio) improving measurement data like this.The top step number that interior formation compound Formation Orbit parameter determines gravity field signal intensity and may measure, actual measurement exponent number then suppresses precision and H_2O maser precision etc. to measure load indicators used decision by outer precision orbit determination precision, inside and outside satellite relative status measuring accuracy, interior satellite nonconservative force.
Star of the present invention is followed the tracks of compound formation gravity field measurement data and is comprised outer Satellite Orbit Determination data, inside and outside satellite relative status measurement data, interstellar distance rate of change data, utilize orbit perturbation principle to recover low order gravity field, utilize star following principle to recover middle and high rank gravity field.The star tracking gravity field measuring system that the present invention is based on interior formation can meet the highest 200 rank gravity fields efficient recovery demand, gravity anomaly precision when 160 rank (corresponding spatial resolution is 125km) is 1mGal, and geoid surface precision is 1cm.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should look protection scope of the present invention.
Claims (4)
1. star follows the tracks of a compound formation earth gravity field measuring system, and it is characterized in that, the interior fleet system number comprised is more than or equal to 2, and wherein each described interior fleet system includes interior satellite and outer satellite platform; Described outer satellite platform comprises outer satellite body and is arranged on the subsystem on described outer satellite body; Be provided with cavity in described outer satellite body, described interior satellite is placed in described cavity;
The subsystem be arranged on described outer satellite body comprises: intersatellite ranging system, outer precision orbit determination system, inside and outside satellite relative status measuring system, interior satellite system latch mechanism, outer measuring system of satellite attitude, outer satellite attitude control system, micromass culture system, data storage cell and data transmission unit;
Described intersatellite ranging system, comprises differential laser interfeerometry ranging instrument between high precision star; Described intersatellite ranging system is used for the interstellar distance rate of change between two adjacent described interior fleet system of precision measurement;
Described outer precision orbit determination system, comprises spaceborne double frequency conventional differential GPS receiver and laser retroreflective array; Described outer precision orbit determination system is used for the accurate orbit determining described outer satellite;
Described inside and outside satellite relative status measuring system, comprises interior satellite normal temperature infrared imaging detector, adopts IR Passive measuring principle; Described inside and outside satellite relative status measuring system is for measuring relative position and the relative velocity of described interior satellite and described outer satellite;
Described interior satellite system latch mechanism, for the locking of described interior satellite and release;
Described outer measuring system of satellite attitude, comprises sun sensor, star sensor and magnetometer; Described outer measuring system of satellite attitude, determines for the described outer attitude of satellite;
Described outer satellite attitude control system, comprises flywheel and magnetic torquer; Described flywheel is used for described outer satellite three-axis attitude stabilization; Described magnetic torquer is used for the unloading of described flywheel;
Described micromass culture system, can provide milli ox magnitude thrust; Described micromass culture system, controls for described outer satellite orbit; Relative status also for described interior satellite and described outer satellite controls;
Described data storage cell, the data of storage comprise in following data one or more or all: the relative status data of interstellar distance rate of change data, described interior satellite and described outer satellite between the orbit determination data of described outer satellite, described adjacent two interior fleet system;
Described data transmission unit, transmits earthward for the data stored by described data storage cell
Described interior satellite is the spherical verification quality that nominal position is positioned at described chamber central; The plation that described interior satellite is 66:34 by volume ratio is formed;
Described interior fleet system adopts the sun synchronization track in morning and evening of 200-300km height, and described track is near polar orbits, and described orbital eccentricity is 0.001;
Interstellar distance between adjacent two described interior fleet system is 50-150km.
2. star according to claim 1 follows the tracks of compound formation earth gravity field measuring system, and it is characterized in that, the cavity in described outer satellite body is spherical cavity, and described cavity diameter is 10 ~ 100 times of described interior satellite diameter.
3. star according to claim 1 and 2 follows the tracks of compound formation earth gravity field measuring system, it is characterized in that, the number of the interior fleet system that described star is followed the tracks of included by compound formation earth gravity field measuring system is two.
4. an application rights requires that the star described in 1 to 3 any one follows the tracks of the method for compound formation earth gravity field measuring system measurement earth gravity field, it is characterized in that, during described interior fleet system operation on orbit, the described interior satellite in two described interior fleet system all runs along pure Attractive Orbit; Then, utilize the relative status measurement data of described outer precision orbit determination data and described interior satellite and described outer satellite, determine the pure Attractive Orbit of described interior satellite; Measure the interstellar distance rate of change between two described interior satellites, carry out inverting with this and obtain middle high-order earth gravity field;
The method of described measurement earth gravity field specifically comprises the steps:
Step 1: the sun synchronization track in morning and evening two described interior fleet system being sent into simultaneously 200 ~ 300km height, follow the tracks of along satellite flight direction composition star and form into columns, interstellar distance is 50 ~ 150km;
Step 2: open the described interior satellite system latch mechanism in two described interior fleet system, is discharged in the cavity of described outer satellite by described interior satellite;
Step 3: for each described interior fleet system, relative position and the relative velocity of described interior satellite and described outer satellite is obtained by described inside and outside satellite relative status measuring system measurement, then outer satellite orbit described in described micromass culture Systematical control is utilized, adjust the relative position of described interior satellite and described outer satellite, the barycenter of described interior satellite and described outer satellite is overlapped, and the star formed based on interior formation follows the tracks of compound formation;
Step 4: for each described interior fleet system, utilizes described sun sensor, described star sensor and described magnetometer to realize attitude measurement, and is supplied to described outer satellite attitude control system;
Step 5: utilize described flywheel to realize described outer satellite three-axis attitude stabilization, utilizes described magnetic torquer to realize the unloading of described flywheel;
Step 6: utilize described spaceborne double frequency conventional differential GPS receiver and described laser retroreflective array, orbit determination measures described outer satellite orbit; Utilize differential laser interfeerometry ranging instrument between described high precision star, measure the interstellar distance rate of change between described two interior fleet system;
Step 7: by the interstellar distance rate of change data between the relative status measurement data of described outer Satellite Orbit Determination data, described interior satellite and described outer satellite, described interior fleet system, be saved in described data storage cell, be the gravity field measurement data of measuring point;
Step 8: repeat step 3 to 7, each measuring point data of continuous coverage, and reach land station by described data transmission unit by under the described gravity field measurement data of each measuring point;
Step 9: after at least completing a Global coverage measurement, reach the described gravity field measurement data of land station under utilizing the process of Earth's gravity field recovery computational tool, inverting obtains earth gravity field model.
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| CN111552003B (en) * | 2020-05-11 | 2020-12-18 | 中国人民解放军军事科学院国防科技创新研究院 | Asteroid gravitational field full-autonomous measurement system and method based on ball satellite formation |
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| CN101915927A (en) * | 2010-04-14 | 2010-12-15 | 清华大学 | Infrared measurement based system and method thereof for determining relative state of inner satellite |
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| 内卫星辐射计效应建模与分析;刘红卫等;《空间科学学报》;20100515;第30卷(第3期);第244页第1栏第9-17行 * |
| 卫星内编队重力场测量关键技术;周辉峰等;《四川兵工学报》;20101225;第31卷(第12期);第137-138页 * |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9599744B2 (en) | 2013-09-29 | 2017-03-21 | Tsinghua University | Method for parsing and calculating performance of satellite gravity field measurement by low-to-low satellite-to-satellite tracking |
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