CN116126946B - Detection data association matching method for continuous maneuvering state satellite-link satellite - Google Patents

Detection data association matching method for continuous maneuvering state satellite-link satellite Download PDF

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CN116126946B
CN116126946B CN202310389892.8A CN202310389892A CN116126946B CN 116126946 B CN116126946 B CN 116126946B CN 202310389892 A CN202310389892 A CN 202310389892A CN 116126946 B CN116126946 B CN 116126946B
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track
satellite
latitude
data
forecast
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CN116126946A (en
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张炜
宋明展
贾立
王秀红
崔文
游经纬
贾熊
高峰
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Chinese People's Liberation Army 32035
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
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    • G06F16/24—Querying
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
    • G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
    • G06F16/29—Geographical information databases
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
    • G06F17/10—Complex mathematical operations
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Abstract

The invention discloses a detection data association matching method of a continuous maneuvering state satellite-link satellite, which comprises the following steps: selecting a satellite chain satellite which is associated and matched with a continuous maneuvering state
Figure ZY_4
The single arc section track determination is carried out on the strip track detection data, and a track root number sequence is obtained; in the first place
Figure ZY_5
The track is used as a reference track, and the number of other tracks is predicted at epoch time
Figure ZY_9
Latitude amplitude angle forecast value at time
Figure ZY_3
The method comprises the steps of carrying out a first treatment on the surface of the Determining a forecast duration
Figure ZY_8
And latitude amplitude angle difference
Figure ZY_11
A satisfied quadratic polynomial; determining a single arc track of the data to be identified to obtain the track number of the corresponding track; forecasting the corresponding track is on
Figure ZY_12
Latitude angle of time
Figure ZY_2
And according to the sum of the track numbers
Figure ZY_7
Determining latitude amplitude angle difference
Figure ZY_10
Duration of forecast
Figure ZY_13
The method comprises the steps of carrying out a first treatment on the surface of the Using quadratic polynomials
Figure ZY_1
Calculated at
Figure ZY_6
And obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite-link satellite according to the theoretical latitude amplitude angle difference of the corresponding orbit. The invention improves the correlation matching effect of the measurement data and the continuous maneuvering state satellite chain satellite.

Description

Detection data association matching method for continuous maneuvering state satellite-link satellite
Technical Field
The invention belongs to the technical field of aerospace measurement and control, and particularly relates to a detection data association matching method of a continuous maneuvering state satellite-link satellite.
Background
The on-orbit operation of the satellite chain satellite mainly comprises four stages of adjustment, orbit lifting, deployment and orbit reduction. During the orbit, the satellite chain satellites all adopt a low-thrust mode to orbit, the maneuvering time of the orbit lifting stage and the orbit descending stage is longer, the maneuvering times are more frequent, and the satellite chain satellites all belong to a continuous maneuvering state. Compared with other uncontrollable space targets, the orbit prediction error of the satellite-chain satellite is larger because accurate control parameters and follow-up orbit control plans cannot be obtained. Taking the precision analysis of the Two-Line Element (Two-Line orbit number) as an example, for the satellite chain satellite in the orbit lifting stage, the forecast 24h position error is generally less than 8km, for the satellite chain satellite in the orbit descending stage, the forecast 24h position error is generally less than 20km, and the forecast confidence period is shorter, generally not more than 24h. Because the satellite chain satellite in the lifting or descending stage is continuously maneuvered, the effect of the non-cooperative orbit prediction result for station measurement tracking is poor, and meanwhile, the confidence of target association matching is greatly reduced, so that autonomous and effective space target cataloging cannot be completed.
The star-chain satellites in a continuous maneuvering state generally finish orbital maneuvering in a grouping mode, but the regularity is not the same, and the regularity of a control strategy is not obvious. For example, the daily orbit amount is substantially the same for each satellite, even for each batch of satellites, but the daily orbit amounts may be different for different batches of satellites. Therefore, the applicability of the traditional measurement data association matching method is low, and a smaller matching threshold value can cause 'omission', so that measurement data is misjudged as a new target; a large matching threshold may result in "ghosting" where a single turn of measurement data is associated with multiple targets and cannot be resolved further.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a detection data association matching method for a continuous maneuvering state satellite chain satellite. The technical problems to be solved by the invention are realized by the following technical scheme:
the invention provides a detection data association matching method of a continuous maneuvering state satellite-link satellite, which comprises the following steps:
selecting a satellite chain satellite which is associated and matched with a continuous maneuvering state
Figure SMS_1
Detecting data of a track and determining a single arc section track to obtain a group of track root sequences, wherein the track root sequences at least comprise +.>
Figure SMS_2
Epoch time of the number of tracks +.>
Figure SMS_3
Near-site argument->
Figure SMS_4
And plain angle->
Figure SMS_5
，/>
Figure SMS_6
，/>
Figure SMS_7
；
In the first place
Figure SMS_8
The track is a reference track, and the number of other tracks is predicted to be +.>
Figure SMS_9
Latitude amplitude forecast value +.>
Figure SMS_10
，/>
Figure SMS_11
；
According to the track root sequence and the latitude amplitude angle forecast value
Figure SMS_12
Determining a forecast duration +.>
Figure SMS_13
Difference from latitude and amplitude>
Figure SMS_14
A satisfied quadratic polynomial;
the method comprises the steps of determining a single arc track of acquired data to be identified to obtain the track number of a track corresponding to the data to be identified, wherein the track number of the corresponding track at least comprises the epoch time of the track corresponding to the data to be identified
Figure SMS_15
Actual near-spot argument->
Figure SMS_16
And the actual straight-ahead point angle +.>
Figure SMS_17
；
Based on the reference track, forecasting the track corresponding to the data to be identified at epoch time
Figure SMS_18
Latitude amplitude forecast value +.>
Figure SMS_19
And according to the number of the tracks corresponding to the data to be identified and the latitude amplitude angle forecast value +.>
Figure SMS_20
Determining latitude amplitude angle difference +.>
Figure SMS_21
Forecast duration +.>
Figure SMS_22
；
According to the forecast duration
Figure SMS_23
Calculating +_at epoch time using the quadratic polynomial>
Figure SMS_24
The theoretical latitude amplitude angle difference of the corresponding orbit is obtained, and the latitude is +.>
Figure SMS_25
And obtaining an association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite.
In one embodiment of the invention, the following is the first
Figure SMS_26
The track is a reference track, and the number of other tracks is predicted to be +.>
Figure SMS_27
Latitude amplitude forecast value +.>
Figure SMS_28
Comprises the steps of:
will be the first
Figure SMS_29
The tracks are used as reference tracks, and the root sequences of other tracks in the root sequence of the tracks are respectively forecasted, wherein the root sequences of the other tracks at least comprise epoch moments of the root of the other tracks>
Figure SMS_30
Near-site argument->
Figure SMS_31
And plain angle->
Figure SMS_32
；
Calculating the number of other tracks at epoch time
Figure SMS_33
Latitude amplitude forecast value +.>
Figure SMS_34
Wherein, the method comprises the steps of, wherein,
Figure SMS_35
。
in one embodiment of the invention, the system is based on the sequence of track root numbers and the latitude argument forecast values
Figure SMS_36
Determining a forecast duration +.>
Figure SMS_37
Difference from latitude and amplitude>
Figure SMS_38
The step of satisfying the quadratic polynomial includes:
for each other track, respectively obtaining from the track root number sequence
Figure SMS_39
Near-spot amplitude at time +.>
Figure SMS_40
And plain angle->
Figure SMS_41
And calculates the latitude amplitude actual value +.>
Figure SMS_42
Wherein->
Figure SMS_43
；
Based on the actual value of the latitude amplitude angle
Figure SMS_46
And the latitude amplitude angle forecast value +.>
Figure SMS_47
Calculating latitude amplitude angle difference of each track>
Figure SMS_50
And based on epoch time ∈ ->
Figure SMS_45
Time of epoch with the reference track +.>
Figure SMS_48
Calculating the forecast time length of other tracks>
Figure SMS_49
Get +.>
Figure SMS_51
And latitude amplitude angle difference +>
Figure SMS_44
Is a sequence of (2);
based on the duration of the forecast
Figure SMS_52
And latitude amplitude angle difference +>
Figure SMS_53
Is fitted to the forecast duration +.>
Figure SMS_54
Difference from latitude and amplitude>
Figure SMS_55
The satisfied quadratic polynomial:
Figure SMS_56
；
wherein A, B, C is a polynomial coefficient.
In one embodiment of the invention, the latitude amplitude angle difference
Figure SMS_57
The forecast duration
Figure SMS_58
。
In one embodiment of the invention, based on the reference track, the track corresponding to the data to be identified is forecasted at the epoch timetLatitude amplitude angle forecast value at time
Figure SMS_59
And according to the number of the tracks corresponding to the data to be identified and the latitude amplitude angle forecast value +.>
Figure SMS_60
Determining latitude amplitude angle difference +.>
Figure SMS_61
Forecast duration +.>
Figure SMS_62
Comprises the steps of:
based on the reference track, forecasting the track corresponding to the data to be identified at epoch time
Figure SMS_63
Track number at time and calculate latitude argument forecast value +.>
Figure SMS_64
The method comprises the steps of carrying out a first treatment on the surface of the Wherein the track number of the corresponding track at least comprises epoch time +.>
Figure SMS_65
、Theoretical perigee argument->
Figure SMS_66
And theoretical mean point angle +.>
Figure SMS_67
，/>
Figure SMS_68
；
At epoch time according to the corresponding tracktThe number of the tracks is calculated, and the actual value of the latitude amplitude angle of the corresponding track is calculated
Figure SMS_69
Wherein->
Figure SMS_70
；
Calculating the actual value of the latitude amplitude angle
Figure SMS_71
And the latitude amplitude angle forecast value +.>
Figure SMS_72
The difference is obtained to obtain the latitude amplitude angle difference
Figure SMS_73
；
Calculating epoch time of the corresponding track
Figure SMS_74
Time of epoch with the reference track +.>
Figure SMS_75
The difference is given to the forecast duration +.>
Figure SMS_76
Wherein->
Figure SMS_77
。
In one embodiment of the invention, according to the forecast duration
Figure SMS_78
Calculating the time of the epoch by using the quadratic polynomialtThe theoretical latitude amplitude angle difference of the corresponding orbit is obtained, and according to the theoretical latitude amplitude angle difference and the latitude amplitude angle difference
Figure SMS_79
The step of obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite comprises the following steps:
calculating the time of the epoch by using the quadratic polynomial according to the following formula
Figure SMS_80
And theoretical latitude amplitude angle difference of the corresponding track:
Figure SMS_81
；
where A, B, C is the polynomial coefficient,
Figure SMS_82
for the epoch instant of said reference track, < >>
Figure SMS_83
Is the theoretical latitude amplitude angle difference;
according to the theoretical latitude amplitude angle difference
Figure SMS_84
And latitude amplitudeAngle difference->
Figure SMS_85
And obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite-link satellite.
In one embodiment of the invention, the angular difference is based on theoretical latitudes
Figure SMS_86
Difference from latitude and amplitude>
Figure SMS_87
The step of obtaining the correlation matching result of the data to be identified and the continuous maneuver state satellite chain satellite comprises the following steps:
calculating theoretical latitude amplitude angle difference
Figure SMS_88
Difference from latitude and amplitude>
Figure SMS_89
Is a difference in (2);
judging whether the difference value is smaller than or equal to a preset threshold value; if yes, the data to be identified are matched with the continuous maneuvering state satellite-link satellite; and otherwise, the data to be identified are not matched with the continuous maneuvering state satellite-link satellite.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a correlation matching method for detection data of a continuous maneuvering state satellite chain, which is based on the rule that the latitude amplitude angular acceleration of the continuous maneuvering state satellite chain is constant, and utilizes the detection data which are successfully correlated and matched to fit the prediction duration
Figure SMS_90
Difference from latitude and amplitude>
Figure SMS_91
Obtaining theoretical latitude amplitude angle difference of the data to be identified, and further comparing the theoretical amplitude angle difference with the actual latitude of the orbit corresponding to the data to be identifiedAmplitude-angle difference->
Figure SMS_92
To confirm whether the data to be identified is successfully matched with the continuous maneuvering state satellite chain satellite. The invention can ensure that the data to be identified is identified quickly, and effectively improves the association matching effect of the measured data and the continuous maneuvering state satellite-link satellite.
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Drawings
FIG. 1 is a flowchart of a method for correlation matching of detection data of a continuously mobile state satellite chain satellite according to an embodiment of the present invention;
FIG. 2 is a diagram of the results of a simulation experiment provided by an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples, but embodiments of the present invention are not limited thereto.
Fig. 1 is a flowchart of a method for correlation matching of detection data of a continuously maneuvering state satellite link satellite according to an embodiment of the present invention. As shown in fig. 1, an embodiment of the present invention provides a method for correlation matching of detection data of a continuously mobile state satellite chain satellite, including:
s1, selecting a satellite chain satellite which is associated and matched with a continuous maneuvering state
Figure SMS_93
Detecting data of the strip track and determining a single arc section track to obtain a group of track root sequences, wherein the track root sequences at least comprise +.>
Figure SMS_94
Epoch time of the number of tracks +.>
Figure SMS_95
Near-site argument->
Figure SMS_96
And plain angle->
Figure SMS_97
，/>
Figure SMS_98
，/>
Figure SMS_99
；
S2, by
Figure SMS_100
The track is a reference track, and the number of other tracks is predicted to be +.>
Figure SMS_101
Latitude amplitude forecast value +.>
Figure SMS_102
，/>
Figure SMS_103
；
S3, forecasting values according to the track root sequence and latitude amplitude angles
Figure SMS_104
Determining a forecast duration +.>
Figure SMS_105
And latitude amplitude angle difference
Figure SMS_106
A satisfied quadratic polynomial;
s4, determining the single-arc track of the acquired data to be identified to obtain the track number of the track corresponding to the data to be identified, wherein the track number at least comprises the epoch time of the track corresponding to the data to be identified
Figure SMS_107
Actual near-spot argument->
Figure SMS_108
And the actual straight-ahead point angle +.>
Figure SMS_109
；
S5, forecasting the time of the calendar moment of the track corresponding to the data to be identified based on the reference tracktLatitude amplitude angle forecast value at time
Figure SMS_110
And according to the number of the tracks corresponding to the data to be identified and the latitude amplitude angle forecast value +.>
Figure SMS_111
Determining latitude amplitude angle difference
Figure SMS_112
Forecast duration +.>
Figure SMS_113
；
S6, according to the forecast time
Figure SMS_114
Calculating +.>
Figure SMS_115
The theoretical latitude amplitude angle difference of the corresponding orbit is equal to the sum of the theoretical latitude amplitude angle difference and the latitude amplitude angle difference +.>
Figure SMS_116
And obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite.
Specifically, in the method for correlation matching of detection data of continuous maneuver state satellite chain satellite provided by the invention, the correlation matched with the continuous maneuver state satellite chain satellite is firstly obtained
Figure SMS_120
The detection data of the strip track is determined and obtained by a single arc section track to obtain a group of track root sequences +.>
Figure SMS_124
Wherein->
Figure SMS_126
，
Figure SMS_118
，/>
Figure SMS_125
Indicate->
Figure SMS_128
Epoch time of strip track->
Figure SMS_129
、/>
Figure SMS_117
、/>
Figure SMS_121
、/>
Figure SMS_123
、/>
Figure SMS_127
And->
Figure SMS_119
Respectively +.>
Figure SMS_122
The number of flat elements of six elements of the strip track is half long axis, eccentricity, inclination, ascent intersection, right ascent, near-place amplitude angle and flat-near point angle. In this embodiment, the number of six elements is obtained by converting the number of known LTE elements, or may be obtained by determining the short arc orbit based on actual measurement data.
Next, in item 1
Figure SMS_133
The track of (2) is a reference track, and the epoch time of other tracks is forecasted>
Figure SMS_131
The root sequence of each other track is +.>
Figure SMS_138
Wherein->
Figure SMS_135
、/>
Figure SMS_144
、/>
Figure SMS_136
、/>
Figure SMS_146
、/>
Figure SMS_145
And->
Figure SMS_147
Respectively represent the%>
Figure SMS_130
The number of the flat elements of the semilong axis, the eccentricity, the dip angle, the ascending intersection point, the right ascent, the near-place amplitude angle and the flat-near point angle of the strip track is calculated according to the sequence of the number of the track
Figure SMS_141
And other individual tracks of the forecast
Figure SMS_137
Calculate->
Figure SMS_140
Latitude amplitude actual value +.>
Figure SMS_143
Latitude amplitude angle forecast value +.>
Figure SMS_148
To further calculate latitude amplitude angle difference +.>
Figure SMS_132
And forecast duration +.>
Figure SMS_142
. In this embodiment, the latitude amplitude angle difference is used +.>
Figure SMS_134
And forecast duration +.>
Figure SMS_139
After fitting the quadratic curve to the composed sequence, the quadratic polynomial satisfied by the two can be determined.
For the data to be identified, the number of the tracks corresponding to the data to be identified can be determined through the single-arc tracks, and it is noted that the track number sequence is not generated because the data to be identified only comprises 1 corresponding track. In this embodiment, the number of tracks includes epoch time of the corresponding track
Figure SMS_149
、The actual semi-major axis, the actual eccentricity, the actual dip angle, the actual ascent point right ascent, the actual perigee amplitude angle and the actual perigee angle. In the steps S5 to S6, the corresponding track is set at the epoch time based on the reference tracktThe latitude amplitude at the time is forecasted to obtain a latitude amplitude forecast value +.>
Figure SMS_150
Thereby determining latitude amplitude angle difference of corresponding track by using the number of tracks>
Figure SMS_151
And will correspond to the epoch time of the tracktEpoch time with reference track ∈ ->
Figure SMS_152
The difference is used as the forecast duration +.>
Figure SMS_153
. The forecast duration +.>
Figure SMS_154
Substituting the theoretical latitude amplitude angle difference into a quadratic polynomial to obtain a theoretical latitude amplitude angle difference, and finally obtaining a theoretical latitude amplitude angle difference and a latitude amplitudeAngle difference->
Figure SMS_155
To determine whether the data to be identified matches the continuous maneuver state satellite chain satellite.
In the above step S2, the following is adopted
Figure SMS_156
The track is a reference track, and the number of other tracks is predicted to be +.>
Figure SMS_157
Latitude amplitude forecast value +.>
Figure SMS_158
Comprises the steps of:
s201, will be
Figure SMS_159
The method comprises the steps of taking a track as a reference track, respectively forecasting the root sequences of other tracks in the track root sequence, wherein the root sequences of the other tracks at least comprise epoch time ∈of the other tracks>
Figure SMS_160
Near-site argument->
Figure SMS_161
And plain angle->
Figure SMS_162
；
S202, calculating the number of other tracks at epoch time
Figure SMS_163
Latitude amplitude forecast value +.>
Figure SMS_164
Wherein, the method comprises the steps of, wherein,
Figure SMS_165
。
optionally, in the step S3,according to the track root sequence and the latitude amplitude angle forecast value
Figure SMS_166
Determining a forecast duration +.>
Figure SMS_167
Difference from latitude and amplitude>
Figure SMS_168
The step of satisfying the quadratic polynomial includes:
s301, respectively obtaining the track number sequence from the track number sequence for other tracks
Figure SMS_169
Near-spot amplitude at time +.>
Figure SMS_170
And plain angle->
Figure SMS_171
And calculates the latitude amplitude actual value +.>
Figure SMS_172
Wherein->
Figure SMS_173
；
S302, based on actual value of latitude amplitude angle
Figure SMS_176
Latitude amplitude forecast value->
Figure SMS_177
Calculating latitude amplitude angle difference of each track>
Figure SMS_181
And based on epoch time ∈ ->
Figure SMS_175
Epoch time with reference track ∈ ->
Figure SMS_178
Calculating the forecast time length of other tracks>
Figure SMS_179
Get +.>
Figure SMS_180
And latitude amplitude angle difference +>
Figure SMS_174
Is a sequence of (2);
s303, based on the forecast duration
Figure SMS_182
And latitude amplitude angle difference +>
Figure SMS_183
Is fitted to the forecast duration +.>
Figure SMS_184
Difference from latitude and amplitude>
Figure SMS_185
The satisfied quadratic polynomial:
Figure SMS_186
；
wherein A, B, C is a polynomial coefficient.
Note that, the latitude amplitude angle difference
Figure SMS_187
Is the actual value of latitude amplitude angle +>
Figure SMS_188
Latitude amplitude forecast value->
Figure SMS_189
The difference, i.e.)>
Figure SMS_190
Forecast duration->
Figure SMS_191
。
Further, in the step S5, the track corresponding to the data to be identified is predicted at the epoch time based on the reference tracktLatitude amplitude angle forecast value at time
Figure SMS_192
And according to the number of the tracks corresponding to the data to be identified and the latitude amplitude angle forecast value +.>
Figure SMS_193
Determining latitude amplitude angle difference +.>
Figure SMS_194
Forecast duration +.>
Figure SMS_195
Comprises the steps of:
s501, forecasting the time of the calendar element corresponding to the data to be identified based on the reference tracktThe number of the tracks at the time and calculating the latitude amplitude angle forecast value
Figure SMS_196
The method comprises the steps of carrying out a first treatment on the surface of the Wherein the track number of the corresponding track at least comprises the epoch time of the corresponding trackt、Theoretical perigee argument->
Figure SMS_197
And theoretical mean point angle +.>
Figure SMS_198
，/>
Figure SMS_199
；
S502, at epoch time according to the corresponding tracktThe number of the tracks is calculated, and the actual value of the latitude amplitude angle of the corresponding track is calculated
Figure SMS_200
Wherein->
Figure SMS_201
；
S503, calculating the actual value of the latitude amplitude angle
Figure SMS_202
Latitude amplitude forecast value->
Figure SMS_203
The difference is obtained to obtain the latitude amplitude angle difference +.>
Figure SMS_204
；
S504, calculating epoch time of the corresponding track
Figure SMS_205
Epoch time with reference track ∈ ->
Figure SMS_206
The difference is given to the forecast duration +.>
Figure SMS_207
Wherein->
Figure SMS_208
；
In the step S6, according to the forecast duration
Figure SMS_209
Calculating at epoch time using quadratic polynomialtThe theoretical latitude amplitude angle difference of the corresponding orbit is equal to the sum of the theoretical latitude amplitude angle difference and the latitude amplitude angle difference +.>
Figure SMS_210
The step of obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite comprises the following steps:
s601, calculating epoch time by using a quadratic polynomial according to the following formulatTheoretical latitude amplitude angle difference of corresponding orbit:
Figure SMS_211
；
where A, B, C is the polynomial coefficient,
Figure SMS_212
is the theoretical latitude amplitude angle difference;
s602, according to the theoretical latitude amplitude angle difference
Figure SMS_213
Difference from latitude and amplitude>
Figure SMS_214
And obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite.
Specifically, a theoretical latitude amplitude angle difference is obtained
Figure SMS_215
And latitude amplitude angle difference +>
Figure SMS_216
Then, the difference value of the two is compared with a preset threshold value, which can be 0.05, for example>
Figure SMS_217
If->
Figure SMS_218
If yes, the data to be identified is considered to be matched with the continuous maneuvering state satellite-link satellite; on the contrary, if->
Figure SMS_219
It indicates that the data to be identified is not matched with the continuously mobile state satellite chain satellite.
The invention provides a continuous maneuvering state satellite-link detection data association matching method by a simulation experiment.
Taking a satellite chain-4457 satellite with NORAD number 53663 as an example, from 10 months 5 days to 10 months 10 days of 2022, the satellite is in an orbit continuous lifting stage for 6 consecutive days, wherein TLE data of the first three days are used as detection data of correlated matching, TLE data of the last three days are used as data to be identified of uncorrelated matching, and the TLE data are simultaneouslyEliminating TLE
Figure SMS_220
The effect of an item is that the item is set to 0 when track prediction is performed. The method comprises the following specific steps:
firstly, 6 pieces of cooperative TLE data of the previous three days of a star chain-4457 satellite are selected as associated matched detection data, and epoch time of each TLE is analyzed
Figure SMS_221
Near-site argument->
Figure SMS_222
And plain angle->
Figure SMS_223
Thereby calculating latitude argument +.>
Figure SMS_224
Figure SMS_225
Simultaneously select item 1, namely ++>
Figure SMS_226
The bar track serves as a reference track.
Then, the epoch moments of other 5 tracks are respectively forecasted by using the reference number to obtain 5 forecasted latitude argument angles
Figure SMS_227
Figure SMS_228
Further, a sequence of ++concerning the forecast duration and amplitude-angle difference as shown in Table 1 was obtained>
Figure SMS_229
。
TABLE 1
Figure SMS_230
Next, the sequences in Table 1 are used
Figure SMS_231
Performing quadratic curve fitting to obtain a quadratic polynomial:
Figure SMS_232
。
further, a theoretical latitude amplitude angle difference of the data to be identified is obtained based on the quadratic polynomial. Calculating corresponding epoch time by using data to be identified three days after satellite chain-4457 satellite
Figure SMS_233
Actual near-spot argument->
Figure SMS_234
And the actual straight-ahead point angle +.>
Figure SMS_235
Obtaining an actual latitude amplitude angle, calculating a forecast latitude amplitude angle according to the associated and matched detection data, and further determining a forecast duration
Figure SMS_236
And actual latitude amplitude angle difference +>
Figure SMS_237
Figure SMS_238
。
Finally, will
Figure SMS_239
Carrying out fitting quadratic polynomial, and calculating to obtain theoretical latitude amplitude angle difference +.>
Figure SMS_240
Further comparing the theoretical latitude amplitude angle difference with the actual latitude amplitude angle difference to obtain a difference value +.>
Figure SMS_241
. As shown in Table 2For the same continuously lifted satellite chain satellite, <' > the same continuously lifted satellite chain satellite, < > the same continuously lifted satellite chain satellite, > for the same continuously lifted satellite chain satellite, < > the same continuously lifted>
Figure SMS_242
Are all less than->
Figure SMS_243
。
TABLE 2
Figure SMS_244
Fig. 2 is a diagram of verification results of a simulation experiment provided by the embodiment of the invention, wherein the horizontal axis represents time, and the vertical axis represents latitude amplitude angle difference. As shown in fig. 2, after a quadratic polynomial determined based on the matched data is drawn, the actual latitude amplitude angle difference of the data to be identified and the fitted quadratic curve can be accurately matched.
According to the above embodiments, the beneficial effects of the invention are as follows:
the invention provides a correlation matching method for detection data of a continuous maneuvering state satellite chain, which is based on the rule that the latitude amplitude angular acceleration of the continuous maneuvering state satellite chain is constant, and utilizes the detection data which are successfully correlated and matched to fit the prediction duration
Figure SMS_245
Difference from latitude and amplitude>
Figure SMS_246
Obtaining a theoretical latitude amplitude angle difference of the data to be identified, and further comparing the theoretical amplitude angle difference with the actual latitude amplitude angle difference of the orbit corresponding to the data to be identified +.>
Figure SMS_247
To confirm whether the data to be identified is successfully matched with the continuous maneuvering state satellite chain satellite. The invention can ensure that the data to be identified is identified quickly, and effectively improves the association matching effect of the measured data and the continuous maneuvering state satellite-link satellite.
In the description of the present invention, a description of the terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Further, one skilled in the art can engage and combine the different embodiments or examples described in this specification.
Although the present application has been described herein in connection with various embodiments, other variations to the disclosed embodiments can be understood and effected by those skilled in the art in practicing the claimed application, from a review of the figures, the disclosure, and the appended claims.
The foregoing is a further detailed description of the invention in connection with the preferred embodiments, and it is not intended that the invention be limited to the specific embodiments described. It will be apparent to those skilled in the art that several simple deductions or substitutions may be made without departing from the spirit of the invention, and these should be considered to be within the scope of the invention.

Claims (7)

1. The method for correlation matching of the detection data of the continuous maneuvering state satellite-link satellite is characterized by comprising the following steps of:
selecting a satellite chain satellite which is associated and matched with a continuous maneuvering state
Figure QLYQS_1
Detecting data of a track and determining a single arc section track to obtain a group of track root sequences, wherein the track root sequences at least comprise +.>
Figure QLYQS_2
Epoch time of number of strip track
Figure QLYQS_3
Near-site argument->
Figure QLYQS_4
And plain angle->
Figure QLYQS_5
，/>
Figure QLYQS_6
，/>
Figure QLYQS_7
；
In the first place
Figure QLYQS_8
The track is a reference track, and the number of other tracks is predicted to be +.>
Figure QLYQS_9
Latitude amplitude forecast value +.>
Figure QLYQS_10
，/>
Figure QLYQS_11
；
According to the track root sequence and the latitude amplitude angle forecast value
Figure QLYQS_12
Determining a forecast duration +.>
Figure QLYQS_13
And latitude amplitude angle difference
Figure QLYQS_14
A satisfied quadratic polynomial;
determining a single arc track of the acquired data to be identified to obtain the track number of the track corresponding to the data to be identified, wherein the track number is the same as the track number of the track corresponding to the data to be identifiedThe track number of the corresponding track at least comprises the epoch time of the track corresponding to the data to be identified
Figure QLYQS_15
Actual near-spot argument->
Figure QLYQS_16
And the actual straight-ahead point angle +.>
Figure QLYQS_17
；
Based on the reference track, forecasting the track corresponding to the data to be identified at epoch timetLatitude amplitude angle forecast value at time
Figure QLYQS_18
And according to the number of the tracks corresponding to the data to be identified and the latitude amplitude angle forecast value +.>
Figure QLYQS_19
Determining latitude amplitude angle difference
Figure QLYQS_20
Forecast duration +.>
Figure QLYQS_21
；
According to the forecast duration
Figure QLYQS_22
Calculating the time of the epoch by using the quadratic polynomialtThe theoretical latitude amplitude angle difference of the corresponding orbit is obtained, and the latitude is +.>
Figure QLYQS_23
And obtaining an association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite.
2. The sustained motor-like of claim 1The detection data association matching method of the state satellite chain satellite is characterized by comprising the following steps of
Figure QLYQS_24
The track is a reference track, and the number of other tracks is predicted to be +.>
Figure QLYQS_25
Latitude amplitude forecast value +.>
Figure QLYQS_26
Comprises the steps of:
will be the first
Figure QLYQS_27
The tracks are used as reference tracks, and the root sequences of other tracks in the root sequence of the tracks are respectively forecasted, wherein the root sequences of the other tracks at least comprise epoch moments of the root of the other tracks>
Figure QLYQS_28
Near-site argument->
Figure QLYQS_29
And plain angle->
Figure QLYQS_30
；
Calculating the number of other tracks at epoch time
Figure QLYQS_31
Latitude amplitude forecast value +.>
Figure QLYQS_32
Wherein, the method comprises the steps of, wherein,
Figure QLYQS_33
。
3. the duration of claim 1The method for correlation matching of detection data of the maneuvering state satellite-link satellite is characterized by comprising the following steps of according to the orbit root sequence and the latitude amplitude angle forecast value
Figure QLYQS_34
Determining a forecast duration +.>
Figure QLYQS_35
And latitude amplitude angle difference
Figure QLYQS_36
The step of satisfying the quadratic polynomial includes:
for each other track, respectively obtaining from the track root number sequence
Figure QLYQS_37
Near-spot amplitude at time +.>
Figure QLYQS_38
And plain angle->
Figure QLYQS_39
And calculates the latitude amplitude actual value +.>
Figure QLYQS_40
Wherein->
Figure QLYQS_41
；
Based on the actual value of the latitude amplitude angle
Figure QLYQS_43
And the latitude amplitude angle forecast value +.>
Figure QLYQS_46
Calculating latitude amplitude angle differences of all tracks
Figure QLYQS_48
And based on epoch time ∈ ->
Figure QLYQS_44
Time of epoch with the reference track +.>
Figure QLYQS_45
Calculating the forecast time length of other tracks
Figure QLYQS_47
Get +.>
Figure QLYQS_49
And latitude amplitude angle difference +>
Figure QLYQS_42
Is a sequence of (2);
based on the duration of the forecast
Figure QLYQS_50
And latitude amplitude angle difference +>
Figure QLYQS_51
Is fitted to the forecast duration by means of least squares
Figure QLYQS_52
Difference from latitude and amplitude>
Figure QLYQS_53
The satisfied quadratic polynomial:
Figure QLYQS_54
；
wherein A, B, C is a polynomial coefficient.
4. The method for correlation matching of detection data of continuously mobile satellite chain satellite according to claim 3, wherein the latitude amplitude angle difference
Figure QLYQS_55
The forecast duration +.>
Figure QLYQS_56
。
5. The method for correlation matching of detection data of continuous mobile state satellite chain satellite according to claim 1, wherein the orbit corresponding to the data to be identified is predicted at epoch time based on the reference orbittLatitude amplitude angle forecast value at time
Figure QLYQS_57
And according to the number of the tracks corresponding to the data to be identified and the latitude amplitude angle forecast value +.>
Figure QLYQS_58
Determining latitude amplitude angle difference
Figure QLYQS_59
Forecast duration +.>
Figure QLYQS_60
Comprises the steps of:
based on the reference track, forecasting the track corresponding to the data to be identified at epoch time
Figure QLYQS_61
Track number at time and calculate latitude argument forecast value +.>
Figure QLYQS_62
The method comprises the steps of carrying out a first treatment on the surface of the Wherein the track number of the corresponding track at least comprises the epoch time of the corresponding trackt、Theoretical perigee argument->
Figure QLYQS_63
And theoretical mean point angle +.>
Figure QLYQS_64
，/>
Figure QLYQS_65
；
At epoch time according to the corresponding track
Figure QLYQS_66
The number of the tracks is calculated, and the actual value of the latitude amplitude angle of the corresponding track is calculated>
Figure QLYQS_67
Wherein, the method comprises the steps of, wherein,
Figure QLYQS_68
；
calculating the actual value of the latitude amplitude angle
Figure QLYQS_69
And the latitude amplitude angle forecast value +.>
Figure QLYQS_70
The difference is obtained to obtain the latitude amplitude angle difference +.>
Figure QLYQS_71
；
Calculating epoch time of the corresponding track
Figure QLYQS_72
Time of epoch with the reference track +.>
Figure QLYQS_73
The difference is given to the forecast duration +.>
Figure QLYQS_74
Wherein->
Figure QLYQS_75
。
6. Detection of continuously motorized state satellite chain satellites as set forth in claim 1The data association matching method is characterized in that according to the forecast time length
Figure QLYQS_76
Calculating +_at epoch time using the quadratic polynomial>
Figure QLYQS_77
The theoretical latitude amplitude angle difference of the corresponding orbit is obtained, and the latitude is +.>
Figure QLYQS_78
The step of obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite chain satellite comprises the following steps:
calculating the time of the epoch by using the quadratic polynomial according to the following formulatAnd theoretical latitude amplitude angle difference of the corresponding track:
Figure QLYQS_79
；
where A, B, C is the polynomial coefficient,
Figure QLYQS_80
for the epoch instant of said reference track, < >>
Figure QLYQS_81
Is the theoretical latitude amplitude angle difference;
according to the theoretical latitude amplitude angle difference
Figure QLYQS_82
Difference from latitude and amplitude>
Figure QLYQS_83
And obtaining the association matching result of the data to be identified and the continuous maneuvering state satellite-link satellite.
7. The sustained maneuver of claim 6The detection data association matching method of the state satellite chain satellite is characterized by comprising the following steps of
Figure QLYQS_84
Difference from latitude and amplitude>
Figure QLYQS_85
The step of obtaining the correlation matching result of the data to be identified and the continuous maneuver state satellite chain satellite comprises the following steps:
calculating theoretical latitude amplitude angle difference
Figure QLYQS_86
Difference from latitude and amplitude>
Figure QLYQS_87
Is a difference in (2);
judging whether the difference value is smaller than or equal to a preset threshold value; if yes, the data to be identified are matched with the continuous maneuvering state satellite-link satellite; and otherwise, the data to be identified are not matched with the continuous maneuvering state satellite-link satellite.
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