CN112731281A - Simulation method for space debris angle measurement data - Google Patents

Simulation method for space debris angle measurement data Download PDF

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CN112731281A
CN112731281A CN202011543968.0A CN202011543968A CN112731281A CN 112731281 A CN112731281 A CN 112731281A CN 202011543968 A CN202011543968 A CN 202011543968A CN 112731281 A CN112731281 A CN 112731281A
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space debris
data
observation
position vector
space
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CN112731281B (en
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候育卓
张晓祥
宋小全
韩中生
林鲲鹏
高卫
陈思
刘卿
王泗宏
赵爽
张大伟
孙福煜
魏锦文
邢宁
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63921 Troops of PLA
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    • 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
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    • G—PHYSICS
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    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
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    • 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
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    • G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
    • G01S19/27—Acquisition or tracking or demodulation of signals transmitted by the system creating, predicting or correcting ephemeris or almanac data within the receiver
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Abstract

The application relates to a space debris angle measurement data simulation method. The method comprises the following steps: the polar motion data, dynamically loaded observation equipment information data, the system error and the random error of dynamic input equipment, and dynamically received and loaded observation plan data of the observation equipment are converted into the position of a station center of the space debris under the J2000 inertial system according to information such as the position and the speed of the space debris under the J2000 inertial system received in real time, so that the horizontal right ascension and the horizontal declination of the space debris under the J2000 inertial system, the right ascension and the declination of the space debris under the equatorial coordinate system of the station center are obtained, the direction and the pitching under the horizontal coordinate are further converted, and the system error, the random error and the outlier are added to generate space debris angle measurement simulation data. The method can observe the space debris in a planned way by loading the observation plan data, ensures the consistency of the simulation environment and the real observation environment in the simulation process, and improves the simulation efficiency of the angle measurement data.

Description

Simulation method for space debris angle measurement data
Technical Field
The application relates to the technical field of space debris detection, in particular to a space debris angle measurement data simulation method.
Background
In many fields such as scientific research, military affairs and the like, space debris needs to be monitored, the position and the change of the space debris in space at each observation moment are measured, the operation track of the space debris is determined, and therefore accurate information of the space debris is obtained. Based on the requirement, the accurate measurement of the space debris is a very important basic link, and the accurate measurement of the space debris is not available, and the track identification, the cataloging and the rail fixing of the space debris and the precise rail fixing of the space debris cannot be realized.
At present, two modes of angle measurement and distance measurement are mainly used for the position accurate measurement of the passive space debris. However, the space debris angle measurement has two modes of absolute positioning and relative positioning, wherein the absolute positioning is to realize the space debris measurement by utilizing the axis system of the telescope, and is influenced by the factors of the processing and adjusting precision of the axis system of the telescope, the atmospheric refraction correction precision, the temperature deformation and the like, and is not influenced by the position precision of the background fixed star. The relative positioning is to realize the measurement of the space debris according to the relative position of the space debris and the background fixed star, the pointing accuracy of the telescope does not directly influence the measurement result, but under the condition that the pointing direction of the telescope and the installation error of the image surface are large, the difference between the theoretical coordinate of the fixed star on the image and the actually measured coordinate of the fixed star on the image is large, especially for the image with the error of the image surface, the difference between the theoretical coordinate of the fixed star at the edge part on the image and the actually measured coordinate on the image is large, and the matching threshold of the given theoretical coordinate and the actually measured coordinate cannot be met, so that the matching failure of the theoretical star map and the actually measured star map of.
There are generally two approaches to obtaining space debris measurement data: actual observation is carried out through an optical telescope; and establishing a mathematical model and obtaining the mathematical model through a simulation means. The first space debris measurement data approach is limited not only by the number of optical telescopes, but also by factors such as the actual observation conditions of the observation station where the optical telescopes are located. The second way for obtaining the space debris measurement data is not limited by the conditions, so that the second way plays an important role in the work of space situation monitoring system design, measurement equipment technical index and item establishment necessity demonstration, station site selection demonstration, orbit determination precision evaluation analysis and the like. However, the angle measurement data obtained by the existing simulation method of the angle measurement data of the space debris has a certain difference with the actually measured angle measurement data, and the problem of poor simulation accuracy exists.
Disclosure of Invention
In view of the above, it is necessary to provide a space debris angle measurement data simulation method, device, computer device and storage medium capable of improving accuracy of a simulation result of space debris angle measurement data.
A method for simulating space debris goniometric data, the method comprising:
dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure BDA0002855187140000021
Receiving ephemeris data of batch space fragments in real time, wherein the ephemeris data comprise serial numbers of the space fragments, simulation time, geocentric positions and velocity vectors under a J2000 inertial system; judging whether the space debris is in an observation plan or not according to the serial number and the simulation time, and obtaining the earth center position vector of the J2000 inertia system space debris of the space debris according to the ephemeris data when the space debris is in the observation plan
Figure BDA0002855187140000022
According to the simulation time, the geocentric position vector of the ground fixation system survey station is obtained
Figure BDA0002855187140000023
Converting into a J2000 inertial system survey station geocentric position vector
Figure BDA0002855187140000024
According to the simulation time and the polar motion data, obtaining a polar motion component (xp, yp) and a UT1 time correction delta UT1 of the simulation time through interpolation calculation;
calculating and acquiring sun earth center position vector of J2000 inertial system of sun according to the simulation time
Figure BDA0002855187140000031
According to the sun geocentric position vector of the J2000 inertial system
Figure BDA0002855187140000032
And the earth center position vector of the J2000 inertial system survey station
Figure BDA0002855187140000033
Obtaining the sun's J2000 inertial system sun station center position vector
Figure BDA0002855187140000034
According to the simulation time, the polar motion component (xp, yp) and the UT1 time correction quantity delta UT1, the position vector of the solar station center of the J2000 inertial system is converted into a position vector
Figure BDA0002855187140000035
Position vector of solar center of station converted into equatorial coordinate system of station center
Figure BDA0002855187140000036
And solar right ascension and declination under the station center equatorial coordinate system;
according to the earth center position vector of the J2000 inertial system survey station
Figure BDA0002855187140000037
And the J2000 inertial system space debris centroid position vector
Figure BDA0002855187140000038
Obtaining the position vector of the station center of the J2000 inertial system space debris of the space debris
Figure BDA0002855187140000039
And the corresponding Ping Chijing
Figure BDA00028551871400000310
Peace declination
Figure BDA00028551871400000311
According to the simulation time, the polar motion component (xp, yp) and the UT1 time correction quantity delta UT1, the J2000 inertial system space debris station center position vector is obtained
Figure BDA00028551871400000312
The station center position vector of the space debris of the station center equatorial coordinate system is obtained through conversion
Figure BDA00028551871400000313
And the right ascension and the declination of the space debris under the station center equatorial coordinate system;
obtaining the space fragment orientation A of the space fragment in the station center horizon coordinate system according to the spatial fragment right ascension and declination in the station center equator coordinate systemdAnd pitch Ed. Obtaining the sun azimuth A of the sun under the station center horizontal coordinate system according to the solar right ascension and declination under the station center equatorial coordinate systemsAnd pitch Es；
Pitching E according to the space debrisdThe sun pitch EsAnd a predetermined minimum observed pitch
Figure BDA00028551871400000314
And sun pitch threshold
Figure BDA00028551871400000315
Judging whether the space debris is optically visible or not, and when the space debris is optically visible, adding a system error, a random error and a field value on the basis of data of a horizontal right ascension and a horizontal declination of the space debris of the J2000 inertial system and data of a space debris position and a pitching under the horizontal coordinate system of the station center according to the angle measurement data system error and the random error to generate angle measurement simulation data of the space debris;
and receiving ephemeris data of new batch space fragments, dynamically updating the information of the observation equipment, dynamically updating an observation plan, and performing angle measurement data simulation on the space fragments in the received ephemeris data until the ephemeris data of the new space fragments are not received any more.
In one embodiment, the method further comprises the following steps: dynamically acquiring observation equipment information in space debris angle measurement data simulation, and dynamically loading an observation plan of space debris after dynamically setting system errors and random error parametersLoading polar motion data into the data, receiving ephemeris data of batch space fragments in real time, and obtaining the geocentric position vector of the earth-solid system observation station of the observation equipment according to the information of the observation equipment
Figure BDA0002855187140000041
The observation equipment information comprises geographical longitude and latitude, astronomical longitude and latitude, altitude, lowest elevation angle and detector view field size of the observation equipment.
In one embodiment, the method further comprises the following steps: dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure BDA0002855187140000042
The system error and random error parameters comprise a system error in the right ascension direction and a system error in the declination direction; random error in the right ascension direction, random error in the declination direction.
In one embodiment, the method further comprises the following steps: the observation plan data comprises a survey station, a fragment number, an observation starting time and an observation ending time; quickly sequencing a plan list in the observation plan data according to the observation starting time to obtain sequenced observation plan data; receiving ephemeris data of batch space fragments in real time, wherein the ephemeris data comprise serial numbers of the space fragments, simulation time, geocentric positions and velocity vectors under a J2000 inertial system; according to the serial number and the simulation time, quickly searching in the sequenced observation plan data through a half-and-half search method, judging whether a space fragment contained in the ephemeris data is in an observation plan or not, and when the space fragment is in the observation plan, obtaining a ground center position vector of the J2000 inertial system space fragment of the space fragment according to the ephemeris data
Figure BDA0002855187140000043
In one embodiment, the method comprises the steps of dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a position vector of a geocentric position of a geostationary observation station of observation equipment according to the observation equipment information
Figure BDA0002855187140000051
Comprises the following steps:
Figure BDA0002855187140000052
wherein ,
Figure BDA0002855187140000053
representing the geocentric position vector of the geostationary survey station; l and B respectively represent the geographical longitude and latitude of the observation equipment; h represents the altitude;
Figure BDA0002855187140000054
P1＝2*P2-P2*P2，P2＝1.0/298.257e0，N,P1,P2intermediate calculation results.
In one embodiment, the method further comprises the following steps: according to the simulation time, the geocentric position vector of the ground fixation system survey station is obtained
Figure BDA0002855187140000055
Converting into a J2000 inertial system survey station geocentric position vector
Figure BDA0002855187140000056
Comprises the following steps:
Figure BDA0002855187140000057
wherein ,
Figure BDA0002855187140000058
representing the earth center position vector of the J2000 inertial system measuring station;
Figure BDA0002855187140000059
representing the geocentric position vector of the geostationary survey station;
Figure BDA00028551871400000510
a polar motion matrix representing the polar motion component (xp, yp);
Figure BDA00028551871400000511
representing an earth rotation matrix, wherein S represents Greenwich mean sidereal time;
Figure BDA00028551871400000512
representing a time matrix; w is the sum of the total weight of the components,
Figure BDA00028551871400000513
zA，θAintermediate variables are respectively:
Figure BDA00028551871400000514
N＝Rx(-εA-Δε)Rz(-Δψ)Rx(εA) Representing a nutation matrix; wherein epsilonAThe yellow meridian nutates and delta epsilon nutates with a crossing angle;
T0is a ephemeris standard epoch (typically 2000.0); t ═ time (date-51544.5)/36525 represents the time interval; date ═ MJD + T denotes the time of observation (unit: day).
In one embodiment, the method further comprises the following steps: calculating and acquiring sun earth center position vector of J2000 inertial system of sun according to the simulation time
Figure BDA0002855187140000061
According to said J2000Position vector of solar geocentric of inertial system
Figure BDA0002855187140000062
And the earth center position vector of the J2000 inertial system survey station
Figure BDA0002855187140000063
Obtaining the sun's J2000 inertial system sun station center position vector
Figure BDA0002855187140000064
Comprises the following steps:
Figure BDA0002855187140000065
wherein ,
Figure BDA0002855187140000066
representing the J2000 inertial frame solar hub position vector;
Figure BDA0002855187140000067
representing the J2000 inertial frame sun geocentric position vector;
Figure BDA0002855187140000068
representing the earth-center position vector of the J2000 inertial system survey station.
In one embodiment, the method further comprises the following steps: when the space debris is pitched EdThe sun pitch EsAnd a predetermined minimum pitch
Figure BDA0002855187140000069
And sun pitch threshold
Figure BDA00028551871400000610
Satisfy the relationship
Figure BDA00028551871400000611
And is
Figure BDA00028551871400000612
The space debris is optically visible; wherein E isdRepresenting the space debris pitch;
Figure BDA00028551871400000613
representing the preset minimum pitch; esRepresenting the sun pitch;
Figure BDA00028551871400000614
representing the sun pitch threshold.
In one embodiment, the method further comprises the following steps: when the space piece is optically visible, according to survey angle data systematic error and random error, add systematic error, random error, wild value on the basis of the data of the horizontal right ascension and the horizontal declination of the space piece of the J2000 inertial system, and the space piece position and pitching under the horizontal coordinate system of the station center, generate the survey angle simulation data of the space piece, include:
when the space debris is optically visible, according to the angle measurement data system error and random error, adding the system error and random error on the basis of the data of the horizontal right ascension and the horizontal declination of the space debris of the J2000 inertial system and the data of the orientation and the pitching of the space debris under the horizontal coordinate system of the station center, and generating the angle measurement simulation data of the space debris as follows:
Figure BDA00028551871400000615
Figure BDA00028551871400000616
wherein ,
Figure BDA00028551871400000617
representing the spatial debris right ascension result value;
Figure BDA00028551871400000618
representing the space debrisDeclination result value; a. thedRepresenting the space debris orientation result value; edRepresenting the space debris pitch result value;
Figure BDA00028551871400000619
representing the J2000 inertial system space debris right ascension;
Figure BDA0002855187140000071
representing the J2000 inertial system space debris flat declination; a. thedRepresents said EdThe space debris orientation under the horizontal coordinate system of the standing center; edRepresenting space debris pitch in the centroidal horizon coordinate system; SE1,SE2Representing the systematic error; RE1,RE2Representing the random error.
According to the simulation method of the space debris angle measurement data, the information such as the position and the speed of the space debris under the J2000 inertial coordinate system received in real time is converted into the position of the station center of the space debris under the J2000 inertial system through the loaded information data of the observation equipment, the system error and the random error of the input equipment and the observation plan data loaded into the observation equipment, the right ascension and the declination of the space debris under the equator coordinate system are obtained according to the position of the station center of the space debris under the J2000 inertial system, and the system error, the random error and the wild value are added on the basis of the right ascension and the declination of the space debris according to the system error and the random error parameters to generate the simulation data of the space debris angle measurement. The method can observe the space debris in a planned way by loading the observation plan data, ensures the consistency of the simulation environment and the real observation environment in the simulation process, and improves the simulation efficiency of the angle measurement data. By adding the system error, the random error and the outlier, the generated space debris angle measurement simulation data is closer to the actually measured angle measurement data. The angle measurement simulation data can be used for cataloging and orbit determination simulation, target matching, target association, collision early warning, space debris orbit evolution and other analysis.
Drawings
FIG. 1 is a schematic flow chart of a simulation method of angle measurement data of space debris in one embodiment;
fig. 2 is a schematic flow chart of a simulation method of space debris angle measurement data in an embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The space debris angle measurement data simulation method provided by the application can be applied to the following application environments. The method comprises the steps of receiving and loading observation plan data of observation equipment according to loaded information data of the observation equipment, system errors and random errors of input equipment, converting information such as the position and the speed of a space fragment under a J2000 inertial coordinate system received in real time into the position of a station center of the space fragment under the J2000 inertial system, obtaining the right ascension and the declination of the space fragment under the equatorial coordinate system of the station center according to the position of the station center of the space fragment under the J2000 inertial system, and adding the system errors, the random errors and wild values on the basis of the right ascension and the declination of the space fragment according to system errors and random error parameters to generate simulation data of the space fragment angle measurement.
In one embodiment, as shown in fig. 1, there is provided a method for simulating space debris goniometric data, comprising the steps of:
102, dynamically obtaining observation equipment information in simulation of angle measurement data of space fragments, dynamically loading observation plan data of the space fragments after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space fragments in real time, and obtaining a position vector of a geocentric position of a geostationary system observation station of the observation equipment according to the observation equipment information
Figure BDA0002855187140000081
Defining a ground fixation coordinate system: the origin is the geocentric, the basic plane is a plane orthogonal to the connecting line of the geocentric and the CIO planode, and the X-axis direction is the intersecting line direction of the basic plane on the Greenwich mean plane. Earth-centered position vector of earth-fixed system survey station
Figure BDA0002855187140000082
In the drawing, R represents a survey station, a superscript F represents a ground-fixed coordinate system, and e represents a geocentric origin.
The observation plan data includes information such as a survey station, a fragment number, an observation start time and an observation end time. In the prior art, when the simulation of the angle measurement of the space debris is performed, all ephemeris data received are simulated, and the information of the measuring station cannot be set, so that the simulation environment of the angle measurement of the space debris is inconsistent with the real observation environment. According to the invention, the observation plan data is dynamically loaded, so that the space debris to be observed is determined, and the pertinence and the effectiveness of simulation are improved; the simulation environment is set according to the observation plan and the dynamically acquired observation equipment information, so that the simulation environment is consistent with the real observation environment, and the accuracy of the simulation result is improved; and the observation plan data can be subjected to preliminary analysis, and the running speed of the whole simulation is improved during simulation.
104, receiving ephemeris data of the batch of space fragments in real time, wherein the ephemeris data comprises the serial number of the space fragments, simulation time, and the geocentric position and the velocity vector under a J2000 inertial system; judging whether the space debris is in the observation plan or not according to the serial number and the simulation time, and obtaining the earth center position vector of the J2000 inertia system space debris of the space debris according to the ephemeris data when the space debris is in the observation plan
Figure BDA0002855187140000091
Epoch inertial coordinate system definition: the origin is the geocentric or the standing center, the basic plane is the equatorial plane of the epoch, the X-axis direction is the direction of the epoch vernalization point, and the epoch is 2000.0 in the text. The ephemeris data of the batch space fragments are received in real time, namely, a plurality of ephemeris data are received at one time, and the data processing speed can be increased. J2000 inertial system space debris geocentric position vector
Figure BDA0002855187140000092
Where r denotes space debris, G denotes a J2000 inertial coordinate system, and e denotes groundThe origin of the heart.
106, according to the simulation time, the earth center position vector of the earth fixation system survey station
Figure BDA0002855187140000093
Converting into a J2000 inertial system survey station geocentric position vector
Figure BDA0002855187140000094
J2000 inertia system survey station earth center position vector
Figure BDA0002855187140000095
In the drawing, R represents a survey station, G represents a J2000 inertial coordinate system, and e represents the geocentric.
And step 108, obtaining the polar motion component (xp, yp) of the simulation time and the UT1 time correction delta UT1 through interpolation calculation according to the simulation time and the polar motion data.
Step 110, calculating and obtaining the sun geocentric position vector of the J2000 inertial system of the sun according to the simulation time
Figure BDA0002855187140000096
From the sun's geocentric position vector of the J2000 inertial system
Figure BDA00028551871400000913
And J2000 inertial system survey station geocentric position vector
Figure BDA0002855187140000097
Obtaining the sun's J2000 inertial system sun station center position vector
Figure BDA0002855187140000098
According to the simulation time, the polar motion component (xp, yp) and the UT1 time correction quantity delta UT1, the position vector of the solar station center of the J2000 inertial system is converted into a position vector
Figure BDA0002855187140000099
Position vector of solar center of station converted into equatorial coordinate system of station center
Figure BDA00028551871400000910
And the solar right ascension and declination under the station center equatorial coordinate system.
J2000 inertial system sun earth center position vector
Figure BDA00028551871400000911
Wherein S represents the sun, G represents the J2000 inertial coordinate system, and e represents the geocentric origin; position vector of solar center of station of J2000 inertial system
Figure BDA00028551871400000912
Wherein S represents the sun, G represents the J2000 inertial coordinate system, and o represents the station center origin; station center equatorial coordinate system solar station center position vector
Figure BDA0002855187140000101
In the drawing, S represents the sun, T represents the equatorial coordinate system of the station center, and o represents the origin of the station center.
The station center equatorial coordinate system is defined: the base plane of the origin station center is a plane parallel to a plane orthogonal to a connecting line of the geocentric horizon and the CIO planode, and the X-axis direction is the instantaneous true spring minute point direction; instantaneous equatorial coordinate system definition: the origin is the geocentric, the basic plane is the true equator, and the X-axis direction is the instantaneous true spring minute point direction.
112, according to the earth center position vector of the measuring station of the J2000 inertial system
Figure BDA0002855187140000102
And J2000 inertial system space debris centroid position vector
Figure BDA0002855187140000103
Obtaining the position vector of the center of the space debris of the J2000 inertia system
Figure BDA0002855187140000104
And the corresponding Ping Chijing
Figure BDA0002855187140000105
Peace declination
Figure BDA0002855187140000106
J2000 inertial system space debris station center position vector
Figure BDA0002855187140000107
Where r represents space debris, G represents the J2000 inertial coordinate system, and o represents the station center origin; ping Chijing
Figure BDA0002855187140000108
In the formula, G represents a J2000 inertial coordinate system, o represents a station center origin, and alpha represents the right ascension; flat declination
Figure BDA0002855187140000109
In the drawing, G represents a J2000 inertial coordinate system, o represents a station center origin, and δ represents declination.
Step 114, according to the simulation time, the polar motion component (xp, yp) and the UT1 time correction quantity delta UT1, the position vector of the J2000 inertial system space debris station center is processed
Figure BDA00028551871400001010
The station center position vector of the space debris of the station center equatorial coordinate system is obtained through conversion
Figure BDA00028551871400001011
And the right ascension and declination of the space debris under the station center equatorial coordinate system.
Station center position vector of station center equatorial coordinate system space debris
Figure BDA00028551871400001012
Where r represents the space debris, T represents the centroid equatorial coordinate system, and o represents the centroid origin.
Step 116, obtaining the space debris orientation A of the space debris in the station level coordinate system according to the spatial debris right ascension and declination in the station center equator coordinate systemdAnd pitch Ed. According to the solar right ascension and declination under the station center equatorial coordinate system, the solar azimuth A of the sun under the station center horizon coordinate system is obtainedsAnd pitch Es。
Space debris orientation AdAnd pitch EdIn (A)Representing orientation, E representing pitch, d representing orientation pitch information of the space debris; solar azimuth AsAnd pitch EsIn(s), the azimuth pitch information of the sun is represented. And obtaining the orientation and pitching information of the celestial body according to the information of the right ascension and the declination of the celestial body.
The horizon coordinate system defines: the origin is the station center, the basic plane is the plane tangent to the earth reference ellipsoid through the observation point of the survey station, and the X-axis direction is the north point direction.
Step 118, pitching E according to the space debrisdSun pitch EsAnd a predetermined minimum observed pitch
Figure BDA0002855187140000111
And sun pitch threshold
Figure BDA0002855187140000112
And judging whether the space debris is optically visible, and when the space debris is optically visible, adding a system error, a random error and a wild value on the basis of data of a horizontal right ascension and a horizontal declination of the space debris in the J2000 inertial system and data of the orientation and the pitching of the space debris in the horizontal coordinate system of the station center according to a system error and a random error of angle measurement data to generate angle measurement simulation data of the space debris.
Figure BDA0002855187140000113
Wherein E represents a threshold value, d represents the lowest observation pitch information corresponding to the space debris,
Figure BDA0002855187140000114
in the equation, E represents a threshold value, and s represents the sun. When the space debris is optically visible, according to system errors and random error parameters, the system errors, the random errors and field values are added on the basis of data of the horizontal right ascension and the horizontal declination of the space debris in the J2000 inertial system, and the space debris orientation and space debris pitching in the horizontal coordinate system of the station center, so that the generated space debris angle measurement simulation data is closer to the actually measured angle measurement data. The outlier is an abnormal value exceeding the statistical rule and is the space fragment of the J2000 inertial systemSome values in the data of the plane right ascension and plane declination, and the spatial patch orientation and spatial patch pitch in the station-centric horizon coordinate system are directly replaced with randomly generated outliers.
And 120, receiving ephemeris data of the new batch of space fragments, dynamically updating the information of the observation device, dynamically updating the observation plan, and performing angle measurement data simulation on the space fragments in the received ephemeris data until the ephemeris data of the new space fragments are not received any more.
Since the observation device actually observed may have a fault, the updating of the information of the observation device should be noted during the simulation. When the observation equipment is unavailable, the simulation system should remove the fault equipment, and only use the available equipment data for simulation, so as to ensure the simulation environment to be consistent with the real observation environment, thereby ensuring the reliability and the simulation degree of the simulation result of the angle measurement data.
According to the simulation method of the space debris angle measurement data, information such as the position and the speed of space debris under a J2000 inertial coordinate system received in real time is converted into the position of a space debris station center under the J2000 inertial system through loaded information data of observation equipment, the system error and the random error of input equipment, and observation plan data of the observation equipment are received and loaded, the right ascension and the declination of the space debris under the station center equatorial coordinate system are obtained according to the position of the space debris station center under the J2000 inertial system, and the system error, the random error and the wild value are added on the basis of the right ascension and the declination of the space debris according to the system error and the random error parameters to generate the simulation data of the space debris angle measurement. The method can be used for carrying out simulation observation on the space debris in a planned way by loading the observation plan data, ensures the consistency of a simulation environment and a real observation environment in the simulation process, and improves the simulation efficiency of the angle measurement data. By adding the system error, the random error and the outlier, the generated space debris angle measurement simulation data is closer to the actually measured angle measurement data. The angle measurement simulation data can be used for cataloging and orbit determination simulation, target matching, target association, collision early warning, space debris orbit evolution and other analysis.
In one embodiment, the method further comprises the following steps: dynamically acquiring nullsThe method comprises the steps of dynamically loading observation plan data of space debris after observation equipment information in inter-debris angle measurement data simulation is dynamically set and system errors and random error parameters are dynamically set, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure BDA0002855187140000121
The observation equipment information comprises geographical longitude and latitude, astronomical longitude and latitude, altitude, lowest elevation angle and detector view field size of the observation equipment.
In one embodiment, the method further comprises the following steps: dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure BDA0002855187140000122
The systematic error and random error parameters comprise systematic errors in the right ascension direction and systematic errors in the declination direction; random error in the right ascension direction, random error in the declination direction.
In one embodiment, the method further comprises the following steps: the observation plan data comprises a survey station, a fragment number, an observation starting time and an observation ending time; quickly sequencing a plan list in the observation plan data according to the observation starting time to obtain sequenced observation plan data; receiving ephemeris data of batch space fragments in real time, wherein the ephemeris data comprises the serial number of the space fragments, simulation time, and geocentric position and velocity vector under a J2000 inertial system; and quickly searching in the sequenced observation plan data by a half-and-half search method according to the serial number and the simulation time, judging whether the space debris contained in the ephemeris data is in the observation plan, and when the space debris is in the observation plan, obtaining the geocentric position vector of the J2000 inertial system space debris of the space debris according to the ephemeris data
Figure BDA0002855187140000131
In one embodiment, the method comprises the steps of dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a position vector of a geocentric position of a ground-based system observation station of observation equipment according to the observation equipment information
Figure BDA0002855187140000132
Comprises the following steps:
Figure BDA0002855187140000133
wherein ,
Figure BDA0002855187140000134
representing the position vector of the geocentric of the earth-fixed system measuring station; l and B respectively represent the geographical longitude and latitude of the observation equipment; h represents the altitude;
Figure BDA0002855187140000135
P1＝2*P2-P2*P2，P2＝1.0/298.257e0，N,P1,P2intermediate calculation results.
In one embodiment, the method further comprises the following steps: according to the simulation time, the earth center position vector of the earth fixation system survey station
Figure BDA0002855187140000136
Converting into a J2000 inertial system survey station geocentric position vector
Figure BDA0002855187140000137
Comprises the following steps:
Figure BDA0002855187140000138
wherein ,
Figure BDA0002855187140000139
representing a J2000 inertial system survey station geocentric position vector;
Figure BDA00028551871400001310
representing the position vector of the geocentric of the earth-fixed system measuring station;
Figure BDA00028551871400001311
a polar motion matrix representing polar motion components (xp, yp);
Figure BDA00028551871400001312
representing an earth rotation matrix, wherein S represents Greenwich mean sidereal time;
Figure BDA00028551871400001313
representing a time matrix; w is the sum of the total weight of the components,
Figure BDA00028551871400001314
zA，θAintermediate variables are respectively:
Figure BDA0002855187140000141
N＝Rx(-εA-Δε)Rz(-Δψ)Rx(εA) Representing a nutation matrix; wherein epsilonAThe yellow meridian nutates and delta epsilon nutates with a crossing angle;
T0is a ephemeris standard epoch (typically 2000.0); t ═ time (date-51544.5)/36525 represents the time interval; date ═ MJD + T denotes the time of observation (unit: day).
In one embodiment, the method further comprises the following steps: calculating and acquiring sun earth center position vector of J2000 inertial system of sun according to simulation time
Figure BDA0002855187140000142
According to J2000 inertiaIs the sun's earth center position vector
Figure BDA0002855187140000143
And J2000 inertial system survey station geocentric position vector
Figure BDA0002855187140000144
Obtaining the sun's J2000 inertial system sun station center position vector
Figure BDA0002855187140000145
Comprises the following steps:
Figure BDA0002855187140000146
wherein ,
Figure BDA0002855187140000147
represents a J2000 inertial frame solar hub position vector;
Figure BDA0002855187140000148
representing a J2000 inertial system sun geocentric position vector;
Figure BDA0002855187140000149
represents the J2000 inertial frame survey station geocentric position vector.
Measuring station geocentric position vector according to J2000 inertial system
Figure BDA00028551871400001410
And J2000 inertial system space debris centroid position vector
Figure BDA00028551871400001411
Obtaining the position vector of the center of the space debris of the J2000 inertia system
Figure BDA00028551871400001412
And calculating the sun's J2000 inertial system sun center position vector
Figure BDA00028551871400001413
The principle of (a) is consistent.
In one embodiment, the method further comprises the following steps: when space debris pitching EdSun pitch EsAnd a predetermined minimum pitch
Figure BDA00028551871400001414
And sun pitch threshold
Figure BDA00028551871400001415
Satisfy the relationship
Figure BDA00028551871400001416
And is
Figure BDA00028551871400001417
When the space debris is optically visible; wherein E isdRepresenting space debris pitch;
Figure BDA00028551871400001418
represents a preset minimum pitch; esRepresenting sun pitch;
Figure BDA00028551871400001419
representing the sun pitch threshold.
In one embodiment, the method further comprises the following steps: when the space debris is optically visible, according to the systematic error and the random error of the angle measurement data, the systematic error, the random error and the field value are added on the basis of the data of the horizontal right ascension and the horizontal declination of the space debris of the J2000 inertial system and the data of the orientation and the pitching of the space debris under the horizontal coordinate system of the station center, so that the angle measurement simulation data of the space debris is generated, and the angle measurement simulation data comprises the following steps:
when the space debris is optically visible, according to the systematic error and the random error of the angle measurement data, the systematic error and the random error are added on the basis of the data of the horizontal right ascension and the horizontal declination of the space debris of the J2000 inertial system and the data of the orientation and the pitching of the space debris under the horizontal coordinate system of the station center, and the angle measurement simulation data of the space debris are generated as follows:
Figure BDA0002855187140000151
Figure BDA0002855187140000152
wherein ,
Figure BDA0002855187140000153
representing the spatial debris right ascension result value;
Figure BDA0002855187140000154
representing the space debris declination result value; a. thedRepresenting a space debris orientation result value; edRepresenting a space debris pitch result value;
Figure BDA0002855187140000155
represents the J2000 inertia system space debris-the right ascension channel;
Figure BDA0002855187140000156
represents the J2000 inertial system space debris flat declination; a. thedRepresents EdThe space debris orientation under the horizontal coordinate system of the standing center; edRepresenting space debris pitch in a horizontal coordinate system of a standing center; SE1,SE2Indicating a systematic error; RE1,RE2Indicating a random error.
Systematic errors, random errors and outliers are inevitable in the real observation process, and error information is added into the simulation result of angle measurement data to ensure the consistency of the simulation value and the real observation value.
In one embodiment, as shown in fig. 2, the simulation method of space debris angle measurement data includes the following steps:
s1: loading information data of the observation equipment; the method comprises the following steps: geographical latitude and longitude of observation device
Figure BDA0002855187140000157
Astronomical latitude and longitude
Figure BDA0002855187140000158
Altitude H, lowest elevation angle
Figure BDA0002855187140000159
Detector field size (V)x，Vy) And equipment availability flags.
S2: polar shift data loading; the method comprises the following steps: each day corresponds to the reduced julian day MJD, the polar motion component (xp, yp) (, UT1 time correction delta UT1, totaling N days of polar motion data.
S3: setting parameters of angle measurement data system difference and random difference; the method comprises the following steps: systematic error SE in the direction of the right ascension1Systematic error SE in declination direction2(ii) a Random error RE in the Chi-meridian direction1Random error RE in declination direction2。
S4: observation plan loading, comprising: station survey, chip number, observation start time and end time.
S5: space debris ephemeris data and geocentric position vector under J2000 inertial system
Figure BDA0002855187140000161
Velocity vector
Figure BDA0002855187140000162
S6: and judging whether the equipment state is updated or not.
S7: and judging whether a new observation plan exists or not.
S8: the earth fixed coordinate system and the J2000 inertial coordinate system are mutually converted; corresponding the coordinate of the survey station to the position vector of the geocentric position under the earth-fixed coordinate system
Figure BDA0002855187140000163
Transforming to geocentric position vector under J2000 inertial coordinate system
Figure BDA0002855187140000164
S9: calculation of sun position and sun geocentric position vector under J2000 inertial system
Figure BDA0002855187140000165
S10: according to the geocentric position vector of the observation equipment under the J2000 inertial coordinate system
Figure BDA0002855187140000166
Earth center position vector of sun under J2000 inertial coordinate system
Figure BDA0002855187140000167
Obtaining the station center position vector of the sun under the J2000 inertial coordinate system
Figure BDA0002855187140000168
Obtaining a station center position vector of the sun under a station center equatorial coordinate system through coordinate conversion
Figure BDA0002855187140000169
S11: according to the geocentric position vector of an observation station under a J2000 inertial coordinate system
Figure BDA00028551871400001610
Center position vector of space debris in J2000 inertial coordinate system
Figure BDA00028551871400001611
Calculating the center position vector of the space debris under the J2000 inertial coordinate system
Figure BDA00028551871400001612
Thereby obtaining the spatial debris station center right ascension and declination under the J2000 inertial coordinate system
Figure BDA00028551871400001613
Figure BDA00028551871400001614
S12: calculating the orientation and the pitch (A) of the space debris under the horizontal coordinate system of the center of the stationd,Ed) Sun azimuth and elevation in the isocenter horizon coordinate SystemUpward (A)s,Es). And judging whether the space debris is in an optical visible state or not according to the given thresholds of the lowest pitch, the solar elevation angle and the like.
S13: if the space debris is optically visible with respect to the observation station, random errors, systematic errors, outliers are added.
S14: outputting the angle measurement data of the space debris.
In further embodiments, S5 through S14 are repeated until no space debris ephemeris data is entered.
It should be understood that, although the steps in the flowchart of fig. 1 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps in fig. 1 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.

Claims (9)

1. A method for simulating space debris angle measurement data is characterized by comprising the following steps:
dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure FDA0002855187130000011
Receiving ephemeris data of a batch of space fragments in real time, wherein the ephemeris data comprises the serial number of the space fragments, simulation time,the geocentric position and velocity vector under the J2000 inertial system; judging whether the space debris is in an observation plan or not according to the serial number and the simulation time, and obtaining the earth center position vector of the J2000 inertia system space debris of the space debris according to the ephemeris data when the space debris is in the observation plan
Figure FDA0002855187130000012
According to the simulation time, the geocentric position vector of the ground fixation system survey station is obtained
Figure FDA0002855187130000013
Converting into a J2000 inertial system survey station geocentric position vector
Figure FDA0002855187130000014
According to the simulation time and the polar motion data, obtaining a polar motion component (xp, yp) and a UT1 time correction delta UT1 of the simulation time through interpolation calculation;
calculating and acquiring sun earth center position vector of J2000 inertial system of sun according to the simulation time
Figure FDA0002855187130000015
According to the sun geocentric position vector of the J2000 inertial system
Figure FDA0002855187130000016
And the earth center position vector of the J2000 inertial system survey station
Figure FDA0002855187130000017
Obtaining the sun's J2000 inertial system sun station center position vector
Figure FDA0002855187130000018
According to the simulation time, the polar motion component (xp, yp) and the UT1 time correction quantity delta UT1, the position vector of the solar station center of the J2000 inertial system is converted into a position vector
Figure FDA0002855187130000019
Position vector of solar center of station converted into equatorial coordinate system of station center
Figure FDA00028551871300000110
And solar right ascension and declination under the station center equatorial coordinate system;
according to the earth center position vector of the J2000 inertial system survey station
Figure FDA00028551871300000111
And the J2000 inertial system space debris centroid position vector
Figure FDA00028551871300000112
Obtaining the position vector of the station center of the J2000 inertial system space debris of the space debris
Figure FDA00028551871300000113
And the corresponding Ping Chijing
Figure FDA00028551871300000114
Peace declination
Figure FDA00028551871300000115
According to the simulation time, the polar motion component (xp, yp) and the UT1 time correction quantity delta UT1, the J2000 inertial system space debris station center position vector is obtained
Figure FDA0002855187130000021
The station center position vector of the space debris of the station center equatorial coordinate system is obtained through conversion
Figure FDA0002855187130000022
And the right ascension and the declination of the space debris under the station center equatorial coordinate system;
according to the right ascension and the declination of the space debris under the station center equatorial coordinate system, obtaining the space debris in the stationSpace debris orientation A under the cardiohorizon coordinate systemdAnd pitch Ed(ii) a Obtaining the sun azimuth A of the sun under the station center horizontal coordinate system according to the solar right ascension and declination under the station center equatorial coordinate systemsAnd pitch Es；
Pitching E according to the space debrisdThe sun pitch EsAnd a predetermined minimum observed pitch
Figure FDA0002855187130000023
And sun pitch threshold
Figure FDA0002855187130000024
Judging whether the space debris is optically visible or not, and when the space debris is optically visible, adding a system error, a random error and a field value on the basis of data of a horizontal right ascension and a horizontal declination of the space debris of the J2000 inertial system and data of a space debris position and a pitching under the horizontal coordinate system of the station center according to the angle measurement data system error and the random error to generate angle measurement simulation data of the space debris;
and receiving ephemeris data of new batch space fragments, dynamically updating the information of the observation equipment, dynamically updating an observation plan, and performing angle measurement data simulation on the space fragments in the received ephemeris data until the ephemeris data of the new space fragments are not received any more.
2. The method according to claim 1, wherein the dynamically acquiring information of the observation device in the simulation of the angle measurement data of the space debris, dynamically loading the observation plan data of the space debris after dynamically setting parameters of system errors and random errors, loading polar shift data, receiving ephemeris data of the batch of space debris in real time, and obtaining the position vector of the geocentric position of the earth-fixed system observation station of the observation device according to the information of the observation device
Figure FDA0002855187130000025
The method comprises the following steps:
dynamically acquiring space debris angle measurement dataObserving equipment information in simulation is dynamically loaded after system error and random error parameters are dynamically set, observing plan data of space debris are dynamically loaded, polar motion data are loaded, ephemeris data of batch space debris are received in real time, and a geocentric position vector of a geostationary observation station of the observing equipment is obtained according to the observing equipment information
Figure FDA0002855187130000026
The observation equipment information comprises geographical longitude and latitude, astronomical longitude and latitude, altitude, lowest elevation angle and detector view field size of the observation equipment.
3. The method according to claim 1, wherein the dynamically acquiring information of the observation device in the simulation of the angle measurement data of the space debris, dynamically loading the observation plan data of the space debris after dynamically setting parameters of system errors and random errors, loading polar shift data, receiving ephemeris data of the batch of space debris in real time, and obtaining the position vector of the geocentric position of the earth-fixed system observation station of the observation device according to the information of the observation device
Figure FDA0002855187130000031
The method comprises the following steps:
dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure FDA0002855187130000032
The system error and random error parameters comprise a system error in the right ascension direction and a system error in the declination direction; random error in the right ascension direction, random error in the declination direction.
4. The method of claim 1, wherein the observation plan data includes a station, a chip number, an observation start time, and an observation end time;
receiving ephemeris data of batch space fragments in real time, wherein the ephemeris data comprise serial numbers of the space fragments, simulation time, geocentric positions and velocity vectors under a J2000 inertial system; judging whether the space debris is in an observation plan or not according to the serial number and the simulation time, and obtaining the earth center position vector of the J2000 inertia system space debris of the space debris according to the ephemeris data when the space debris is in the observation plan
Figure FDA0002855187130000033
The method comprises the following steps:
quickly sequencing a plan list in the observation plan data according to the observation starting time to obtain sequenced observation plan data;
receiving ephemeris data of batch space fragments in real time, wherein the ephemeris data comprise serial numbers of the space fragments, simulation time, geocentric positions and velocity vectors under a J2000 inertial system; according to the serial number and the simulation time, quickly searching in the sequenced observation plan data through a half-and-half search method, judging whether a space fragment contained in the ephemeris data is in an observation plan or not, and when the space fragment is in the observation plan, obtaining a ground center position vector of the J2000 inertial system space fragment of the space fragment according to the ephemeris data
Figure FDA0002855187130000041
5. The method according to claim 1, wherein the dynamically acquiring information of the observation device in the simulation of the angle measurement data of the space debris, dynamically loading the observation plan data of the space debris after dynamically setting parameters of system errors and random errors, loading polar shift data, receiving ephemeris data of the batch of space debris in real time, and obtaining the position vector of the geocentric position of the earth-fixed system observation station of the observation device according to the information of the observation device
Figure FDA0002855187130000042
The method comprises the following steps:
dynamically acquiring observation equipment information in space debris angle measurement data simulation, dynamically loading observation plan data of space debris after dynamically setting system errors and random error parameters, loading polar motion data, receiving ephemeris data of batch space debris in real time, and obtaining a geocentric position vector of a geostationary system observation station of observation equipment according to the observation equipment information
Figure FDA0002855187130000043
Comprises the following steps:
Figure FDA0002855187130000044
wherein ,
Figure FDA0002855187130000045
representing the geocentric position vector of the geostationary survey station; l and B respectively represent the geographical longitude and latitude of the observation equipment; h represents the altitude;
Figure FDA0002855187130000046
P1＝2*P2-P2*P2，P2＝1.0/298.257e0，N,P1,P2intermediate calculation results.
6. The method of claim 5, wherein the geocentric location vector of the geostationary survey station is determined based on the simulation time
Figure FDA0002855187130000047
Converting into a J2000 inertial system survey station geocentric position vector
Figure FDA0002855187130000048
The method comprises the following steps:
according to the simulation time, fixing the groundIs the location vector of the earth center of the survey station
Figure FDA0002855187130000049
Converting into a J2000 inertial system survey station geocentric position vector
Figure FDA00028551871300000410
Comprises the following steps:
Figure FDA00028551871300000411
wherein ,
Figure FDA00028551871300000412
representing the earth center position vector of the J2000 inertial system measuring station;
Figure FDA00028551871300000413
representing the geocentric position vector of the geostationary survey station;
Figure FDA00028551871300000414
a polar motion matrix representing the polar motion component (xp, yp);
Figure FDA0002855187130000051
representing an earth rotation matrix, wherein S represents Greenwich mean sidereal time;
Figure FDA0002855187130000052
representing a time matrix; w is the sum of the total weight of the components,
Figure FDA0002855187130000053
zA，θAintermediate variables are respectively:
Figure FDA0002855187130000054
N＝Rx(-εA-Δε)Rz(-Δψ)Rx(εA) Representing a nutation matrix; wherein epsilonAThe yellow meridian nutates and delta epsilon nutates with a crossing angle;
T0is a ephemeris standard epoch (typically 2000.0); t ═ time (date-51544.5)/36525 represents the time interval; date ═ MJD + T denotes the time of observation (unit: day).
7. The method of claim 6, wherein the calculating and obtaining the sun's J2000 inertial system sun geocentric position vector according to the simulation time
Figure FDA0002855187130000055
According to the sun geocentric position vector of the J2000 inertial system
Figure FDA0002855187130000056
And the earth center position vector of the J2000 inertial system survey station
Figure FDA0002855187130000057
Obtaining the sun's J2000 inertial system sun station center position vector
Figure FDA0002855187130000058
The method comprises the following steps:
calculating and acquiring sun earth center position vector of J2000 inertial system of sun according to the simulation time
Figure FDA0002855187130000059
According to the sun geocentric position vector of the J2000 inertial system
Figure FDA00028551871300000510
And the earth center position vector of the J2000 inertial system survey station
Figure FDA00028551871300000511
Obtaining the sun station center position of the J2000 inertial system of the sun(Vector)
Figure FDA00028551871300000512
Comprises the following steps:
Figure FDA00028551871300000513
wherein ,
Figure FDA00028551871300000514
representing the J2000 inertial frame solar hub position vector;
Figure FDA00028551871300000515
representing the J2000 inertial frame sun geocentric position vector;
Figure FDA00028551871300000516
representing the earth-center position vector of the J2000 inertial system survey station.
8. The method of claim 1, wherein the space debris pitch E is based ondThe sun pitch EsAnd a predetermined minimum observed pitch
Figure FDA00028551871300000517
And sun pitch threshold
Figure FDA00028551871300000518
Determining whether the space debris is optically visible, comprising:
when the space debris is pitched EdThe sun pitch EsAnd a predetermined minimum pitch
Figure FDA0002855187130000061
And sun pitch threshold
Figure FDA0002855187130000062
Satisfy the relationship
Figure FDA0002855187130000063
And is
Figure FDA0002855187130000064
The space debris is optically visible; wherein E isdRepresenting the space debris pitch;
Figure FDA0002855187130000065
representing the preset minimum pitch; esRepresenting the sun pitch;
Figure FDA0002855187130000066
representing the sun pitch threshold.
9. The method according to claim 1, wherein the space debris goniometric simulation data includes a space debris right ascension result value, a space debris declination result value, a space debris orientation result value, and a space debris pitch result value;
when the space piece is optically visible, according to survey angle data systematic error and random error, add systematic error, random error, wild value on the basis of the data of the horizontal right ascension and the horizontal declination of the space piece of the J2000 inertial system, and the space piece position and pitching under the horizontal coordinate system of the station center, generate the survey angle simulation data of the space piece, include:
when the space debris is optically visible, according to the angle measurement data system error and random error, adding the system error and random error on the basis of the data of the horizontal right ascension and the horizontal declination of the space debris of the J2000 inertial system and the data of the orientation and the pitching of the space debris under the horizontal coordinate system of the station center, and generating the angle measurement simulation data of the space debris as follows:
Figure FDA0002855187130000067
Figure FDA0002855187130000068
wherein ,
Figure FDA0002855187130000069
representing the spatial debris right ascension result value;
Figure FDA00028551871300000610
representing the space debris declination result value; a. thedRepresenting the space debris orientation result value; edRepresenting the space debris pitch result value;
Figure FDA00028551871300000611
representing the J2000 inertial system space debris right ascension;
Figure FDA00028551871300000612
representing the J2000 inertial system space debris flat declination; a. thedRepresents said EdThe space debris orientation under the horizontal coordinate system of the standing center; edRepresenting space debris pitch in the centroidal horizon coordinate system; SE1,SE2Representing the systematic error; RE1,RE2Representing the random error.
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