CN116184454B - Satellite orbit parameter determination method, device, equipment and readable storage medium - Google Patents
Satellite orbit parameter determination method, device, equipment and readable storage medium Download PDFInfo
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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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- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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Abstract
The application discloses a satellite orbit parameter judging method, device, equipment and readable storage medium, wherein when receiving the target orbit instantaneous root corresponding to a satellite, the method calculates the starting time of the satellite entering the target receiving range of a ground receiving station in the same circle number on the same day based on the target orbit instantaneous root and the latest orbit instantaneous root in the normal orbit instantaneous root received in the k day respectively, obtains the first starting time and the second starting time, calculates the absolute value of the difference value between the first starting time and the second starting time, obtains the time difference, finally judges whether the target orbit instantaneous root is normal by judging whether the time difference is in a reasonable time range or not according to a preset standard time difference threshold, and because the judgment of whether the target orbit instantaneous root is normal or not is carried out when the target orbit instantaneous root is received, the method can not report to a data receiving and processing system when the judgment is abnormal, and avoid data receiving failure and processing errors.
Description
Technical Field
The present invention relates to the field of internet technologies, and in particular, to a satellite orbit parameter determination method, device, apparatus and readable storage medium.
Background
The instantaneous orbit root number refers to the orbit root number corresponding to the instantaneous orbit ellipse which changes with time when the spacecraft flies in space, and is described by six parameters, the instantaneous orbit root number is pushed to a receiver by a sender every day, the receiver directly reports the instantaneous orbit root number to a data receiving and processing system for working after receiving the instantaneous orbit root number pushed by the sender, the instantaneous satellite orbit root number has significance for satellite data receiving and processing, the instantaneous orbit root number is used for forecasting the time range of a satellite passing through a ground receiving station for the satellite data receiving system, the switching-on time of the satellite to the ground data transmission and the switching-on time of an antenna of the ground station are calculated, and the instantaneous orbit root number is used for carrying out orbit division and positioning calculation on satellite observation data for the satellite data processing system.
However, since the receiving side receives the instantaneous number of orbits pushed by the transmitting side and reports the instantaneous number of orbits to the data receiving and processing system for working, when the received instantaneous number of orbits is abnormal, the satellite data receiving and processing system cannot predict the correct time range of the satellite passing through the ground receiving station, and further cannot normally calculate the on-off time of the satellite to the ground data transmission and the on-off time of the ground station antenna, so that orbit division and positioning calculation cannot be performed on satellite observation data, data receiving time is missed, data loss is caused, and if emergency situations occur, for example, the transmitting side pushes the predicted instantaneous number of orbits to the receiving side before controlling the satellite to avoid space debris collision to perform temporary orbit control maneuver, but at the moment, the satellite orbit is not changed, and data receiving failure and processing errors are also caused.
Disclosure of Invention
In view of this, the present application provides a method, an apparatus, a device, and a readable storage medium for determining satellite orbit parameters, which are used for solving the problems of failure data reception and processing error caused by the fact that when a receiver receives an instantaneous orbit number pushed by a sender, the instantaneous orbit number is directly reported to a data receiving and processing system for working, and when the received instantaneous orbit number is abnormal.
In order to achieve the above object, the following solutions have been proposed:
a satellite orbit parameter determination method, comprising:
acquiring parameters of a ground receiving station corresponding to a satellite to be judged;
when the target instantaneous orbit root number corresponding to the satellite is received, calculating a first starting time of the satellite entering a target receiving range of the ground receiving station on the target circle number on the x th day based on the target instantaneous orbit root number and the parameter, wherein the number of days for receiving the target instantaneous orbit root number corresponding to the satellite for the first time is 1 st day, x is less than or equal to m, and m is the number of days for receiving the target instantaneous orbit root number;
calculating a second starting time of the satellite entering the target receiving range on the x-th day on the basis of the latest track instantaneous root number in the normal track instantaneous root number received on the k-th day and the parameters, wherein k is less than or equal to m;
calculating the absolute value of the difference value between the first starting time and the second starting time to obtain a time difference;
judging whether the time difference is in a reasonable time range or not by referring to a preset standard time difference threshold;
if yes, judging that the instantaneous root number of the target track is normal.
Preferably, x=k < m;
the determining process of the standard time difference threshold comprises the following steps:
calculating absolute values of differences of starting times of the satellites entering the target receiving range on the previous day or the next day of two days sequentially based on the latest and normal two track instantaneous numbers received on two continuous days from the 1 st day to the m-1 st day to obtain m-2 differences;
when m is not greater than n, calculating the product of the average value of the m-2 differences and m-k to obtain a standard time difference threshold value, wherein n is the revisit period of the satellite;
and when m is larger than n, calculating the product of the m-n difference value in the m-2 difference values to the average value of the m-2 difference values and m-k to obtain a standard time difference threshold.
Preferably, x=k < m;
the determining process of the standard time difference threshold comprises the following steps:
calculating absolute values of differences of starting times of the satellites entering the target receiving range on the previous day or the next day of two days sequentially based on the latest and normal two track instantaneous numbers received on two continuous days from the 1 st day to the m-1 st day to obtain m-2 differences;
when m is not greater than n, calculating the product of the average value of the m-2 differences and m-k to obtain an initial standard time difference threshold value, wherein n is the revisit period of the satellite;
when m is larger than n, calculating the product of the m-n difference value in the m-2 difference values to the average value of the m-2 difference values and m-k to obtain an initial standard time difference threshold;
calculating the difference value between the maximum difference value and the minimum difference value in the m-2 difference values to obtain a compensation value;
and calculating the sum of the initial standard time difference threshold and the compensation value to obtain the standard time difference threshold.
Preferably, the determining whether the time difference is within a reasonable time range with reference to a preset standard time difference threshold includes:
judging whether the standard time difference threshold is not smaller than the time difference;
if yes, determining that the time difference is in a reasonable time range;
if not, determining that the time difference is not in a reasonable time range.
Preferably, when m is greater than n, m-n is less than or equal to k < m.
Preferably, the parameters include: coordinates of the receiving antenna, elevation range and azimuth range.
Preferably, after determining that the target track transient root number is normal, the method further comprises:
and reporting the instantaneous number of the target track to a data receiving and processing system.
A satellite orbit parameter determination device, comprising:
the parameter acquisition unit is used for acquiring parameters of a ground receiving station corresponding to the satellite to be judged;
the first starting time calculation unit is used for calculating the first starting time of the satellite entering the target receiving range of the ground receiving station on the target circle number on the x th day based on the target track instantaneous root number and the parameter when the target track instantaneous root number corresponding to the satellite is received, wherein the number of days for receiving the track instantaneous root number corresponding to the satellite for the first time is 1 st day, x is less than or equal to m, and m is the number of days for receiving the target track instantaneous root number;
a second start time calculation unit, configured to calculate a second start time of the satellite entering the target receiving range on the target circle number on the x-th day based on the latest track instantaneous root number among the normal track instantaneous root numbers received on the k-th day and the parameter, where k is less than or equal to m;
a time difference calculating unit, configured to calculate an absolute value of a difference between the first start time and the second start time, to obtain a time difference;
the time difference judging unit is used for referring to a preset standard time difference threshold value to judge whether the time difference is in a reasonable time range or not;
if yes, executing the following steps of a target track instantaneous root number judging unit;
and the judging normal unit is used for judging that the instantaneous root number of the target track is normal.
A satellite orbit parameter determination device comprising a memory and a processor;
the memory is used for storing programs;
the processor is configured to execute the program to implement each step of the satellite orbit parameter determination method.
A readable storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of the aforementioned satellite orbit parameter determination method.
According to the satellite orbit parameter judging method, when the target orbit instantaneous root corresponding to the satellite to be judged is received, the latest orbit instantaneous root in the normal orbit instantaneous root received on the kth day is calculated based on the target orbit instantaneous root and the latest orbit instantaneous root in the normal orbit instantaneous root received on the kth day respectively, the starting time of the satellite in the same circle number entering the target receiving range of the ground receiving station on the same day is calculated, the first starting time and the second starting time are obtained, the absolute value of the difference value between the first starting time and the second starting time is calculated, the time difference is obtained, finally the preset standard time difference threshold is consulted, whether the target orbit instantaneous root is normal or not is judged by judging whether the time difference is within a reasonable time range, and if the target orbit instantaneous root is not normal, the error is not processed due to the fact that the target orbit instantaneous root is received on the kth day, the target orbit instantaneous root is not normally received, and the system is not normally processed when the error is judged, and the error is not normally received due to the fact that the target orbit instantaneous root is not received is judged.
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In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present application, and that other drawings may be obtained according to the provided drawings without inventive effort to a person skilled in the art.
Fig. 1 is a flowchart of a satellite orbit parameter determination method disclosed in an embodiment of the present application;
FIG. 2a is a schematic diagram of a satellite and ground receiving station according to an example embodiment of the present application;
fig. 2b is a schematic diagram of a receiving range of a ground receiving station according to an embodiment of the present application;
fig. 3 is a schematic structural diagram of a satellite orbit parameter determining device according to an embodiment of the present disclosure;
fig. 4 is a block diagram of a hardware structure of a satellite orbit parameter determination device according to an embodiment of the present application.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
The scheme can be realized based on the terminal with the data processing capability, and the terminal can be a computer, a server, a cloud end and the like.
An embodiment of the present application provides a satellite orbit parameter determination scheme, and a satellite orbit parameter determination method of the present application is described below with reference to fig. 1, where the method may include:
and step S100, acquiring parameters of a ground receiving station corresponding to the satellite to be judged.
Specifically, the satellite to be determined is a satellite whose corresponding instantaneous orbit number is required to be determined whether or not is normal, the instantaneous orbit number is the corresponding orbit number of the instantaneous orbit ellipse which changes with time when the spacecraft flies in space, and can be described by six parameters including a semi-long axis of orbit, an orbit eccentricity, an orbit inclination angle, an ascending intersection point, a near-point amplitude angle and a flat-near angle, each satellite corresponds to a corresponding ground receiving station, the ground receiving station is used for data transmission with the satellite, for a fixed satellite, the receiving range of the corresponding ground receiving station is fixed, in the flying process, the satellite can perform data transmission with the satellite when entering the receiving range of the ground receiving station, as shown in fig. 2a, the satellite a flies around the earth on the corresponding orbit, and B is the corresponding ground receiving station, as shown in fig. 2B, the network structure is the receiving range of the ground receiving station B for the satellite, when the satellite a starts entering the receiving range of the ground receiving station B, the satellite can start data transmission with the ground receiving station B, and the embodiment of the application finds that the satellite can calculate the receiving range of the satellite based on the corresponding instantaneous orbit number and the corresponding satellite.
And step S110, when the target track instantaneous root number corresponding to the satellite is received, calculating a first starting time of the satellite entering the target receiving range of the ground receiving station on the target circle number on the x day based on the target track instantaneous root number and the parameter.
The number of days for receiving the instantaneous number of orbits corresponding to the satellite for the first time is 1 st day, x is less than or equal to m, and m is the number of days for receiving the instantaneous number of the target orbits.
Specifically, the target instantaneous root number is an instantaneous root number of an orbit which needs to be determined whether to be normal, when the target instantaneous root number corresponding to the satellite is received, if the instantaneous root number is directly reported to the data receiving and processing system, data receiving and processing may fail, so that the determination of whether to be normal should be performed on the target instantaneous root number, so that when the determination is abnormal, the instantaneous root number can not be reported to the data receiving and processing system, since the starting time of the satellite entering the receiving range of the corresponding ground receiving station can be calculated based on the instantaneous root number of the orbit corresponding to the satellite and the parameters of the ground receiving station corresponding to the satellite, the first starting time of the satellite entering the target receiving range of the ground receiving station on the x-th day can be calculated based on the instantaneous root number of the orbit and the acquired parameters of the ground receiving station, since the satellite enters the target receiving range of the ground receiving station multiple times per day, a circle number may be set for each time the satellite enters the target receiving range of the ground receiving station, for example, the satellite enters the target receiving range twice per day, then the first entry per day may be set to the first circle number, the second entry may be set to the second circle number, or the first entry of the first day may be set to the first circle number, the second entry of the first day may be set to the second circle number, the first entry of the second day may be set to the third circle number, the first entry of the second day may be set to the fourth circle number, and so on, based on this, a target circle number may be selected, and the first start time of the satellite entering the target receiving range of the ground receiving station at the target circle number may be calculated.
Step S120, calculating a second start time of the satellite entering the target receiving range on the target circle number on the x-th day based on the latest track instantaneous root number of the normal track instantaneous root numbers received on the k-th day.
Wherein k is less than or equal to m.
Specifically, k may be any one of days 1 to m, after calculating the first starting time of the target receiving range of the ground receiving station for the x-th satellite in the target receiving range of the ground receiving station based on the target instantaneous root number and the parameter, the latest instantaneous root number of the normal orbit received by the k-th satellite in the first starting time may be selected again, and the second starting time of the x-th satellite in the target receiving range may be calculated again, so as to determine whether the target instantaneous root number is normal based on the second starting time and the first starting time, and since the target instantaneous root number corresponding to the satellite is determined to be normal when the target instantaneous root number corresponding to the satellite is received, all the instantaneous root numbers of the orbit received before the current moment are the instantaneous root numbers of the orbit determined to be normal, and since the instantaneous root numbers of the orbit are received daily, in order to ensure the accuracy of the second starting time, the latest instantaneous root number of the normal orbit received by the k-th satellite is selected, and in order to determine whether the target instantaneous root number of the orbit received by the k-th satellite is normal, the instantaneous root number of the target satellite is calculated again in the target receiving range.
Step S130, calculating the absolute value of the difference between the first starting time and the second starting time to obtain a time difference.
Specifically, after the first starting time and the second starting time are calculated, the absolute value of the difference value of the first starting time and the second starting time is calculated, and the time difference is obtained, so that whether the instantaneous root number of the target track is normal or not is judged based on the time difference.
And step 140, referring to a preset standard time difference threshold, judging whether the time difference is within a reasonable time range.
Specifically, the embodiment of the application finds that for a satellite, the starting time of the satellite entering the target receiving range of the ground receiving station in the same circle number on the same day is different based on two corresponding normal track instantaneous numbers and the corresponding parameters of the ground receiving station, but the time difference of the two starting times is in a reasonable time range, so that the embodiment of the application presets a standard time difference threshold value for judging whether the time difference of the satellite entering the target receiving range in the same circle number is in a reasonable time range or not based on the latest track instantaneous numbers in the received target track instantaneous numbers and the normal track instantaneous numbers received in the kth day.
If yes, the following step S150 is executed.
And step S150, judging that the instantaneous number of the target track is normal.
Specifically, since the first starting time and the second starting time are obtained by calculating the starting time of the satellite entering the target receiving range of the ground receiving station in the same circle number on the same day based on the target track instantaneous root number and the latest track instantaneous root number in the normal track instantaneous root number received on the kth day respectively, if the target track instantaneous root number is abnormal, referring to a preset standard time difference threshold, the calculated time difference between the first starting time and the second starting time is not in a reasonable time range, and only if the judging time difference is in the reasonable time range, the target track instantaneous root number can be judged to be normal.
According to the satellite orbit parameter judging method, when the target orbit instantaneous root corresponding to the satellite to be judged is received, the latest orbit instantaneous root in the normal orbit instantaneous root received on the k-th day is calculated based on the target orbit instantaneous root respectively, the starting time of the satellite entering the target receiving range of the ground receiving station on the same circle number on the same day is obtained, the first starting time and the second starting time are calculated, the absolute value of the difference value between the first starting time and the second starting time is calculated, the time difference is obtained, finally the preset standard time difference threshold is consulted, whether the target orbit instantaneous root is normal or not is judged by judging whether the time difference is within a reasonable time range, and as the second starting time is calculated based on the latest orbit instantaneous root in the normal orbit instantaneous root received on the k-th day, if the target orbit instantaneous root is abnormal, the time difference threshold is consulted, the time difference between the first starting time and the second starting time calculated on the basis of the target orbit instantaneous root exceeds a reasonable time range, and only when the time difference is judged to be within the reasonable time range, the target orbit instantaneous root is judged to be normal or not, and the error is avoided from being received on the target orbit instantaneous root when the normal orbit instantaneous root is judged to be normal or not received.
Optionally, the parameters of the above ground receiving station may include: coordinates of the receiving antenna, elevation range and azimuth range.
Optionally, after determining that the target track transient root number is normal in the step S160, the method may further include:
and reporting the instantaneous number of the target track to a data receiving and processing system.
Specifically, after the target instantaneous root number is judged to be normal, the target track instantaneous root number can be reported to the data receiving and processing system for working so as to ensure that the data is successfully received and correctly processed.
Optionally, in the embodiment of the present application, it is found that, when the start time of the receiving range of the ground receiving station corresponding to the satellite is calculated based on the instantaneous number of orbits corresponding to the satellite, the closer the number of days of receiving the instantaneous number of orbits is to the number of days of the satellite entering the receiving range, the more accurate the calculated start time is, for example, the more accurate the calculated start time is based on the instantaneous number of orbits corresponding to the satellite, among two start times obtained by calculating the instantaneous number of orbits corresponding to the satellite, in the receiving range of the ground receiving station, based on the instantaneous number of orbits corresponding to the satellite, and the latest instantaneous number of orbits corresponding to the satellite, in the first day, and the latest instantaneous number of orbits corresponding to the third day, respectively, so that the calculated second start time is the most accurate, and whether the instantaneous number of orbits corresponding to the satellite entering the target receiving range is the target is the most accurate or not is determined based on the first start time and the second instantaneous number of orbits, which is the most accurate.
Alternatively, x may be x=m.
On the basis of the above embodiment, it is found that, in order to determine the standard time difference threshold, the embodiment of the present application may first determine the time difference threshold of two start times corresponding to one day in two days, that is, the standard time difference threshold of one day in interval, which is calculated based on the two latest and normal instantaneous track numbers received in one day in interval, and then determine the standard time difference threshold on the basis, and based on this, the embodiment of the present application provides two alternative manners of determining the standard time difference threshold, which are respectively:
first kind:
and calculating the absolute value of the difference value of the starting time of the satellite entering the target receiving range on the previous day or the next day of two days based on the latest and normal instantaneous root numbers of the two tracks received on two continuous days from the 1 st day to the m-1 st day, so as to obtain m-2 difference values.
Specifically, from day 1 to day m-1, the absolute value of the difference in the start time of the satellite entering the target reception range on the previous or subsequent one of the two days is calculated based on the latest and normal instantaneous root number received on the two consecutive days in turn, for example, the start time t of the satellite entering the target reception range on day 1 or day 2 is calculated based on the latest and normal instantaneous root number received on day 1 1 Calculating the starting time t of the satellite entering the target receiving range on the 1 st or 2 nd day based on the latest and normal track instantaneous number received on the 2 nd day 1 ' calculating t 1 And t 1 The absolute value of the difference' gives DeltaT 1 Calculating the start time t of the satellite entering the target receiving range on day 2 or day 3 based on the latest and normal instantaneous number of orbits received on day 2 2 Calculating the starting time t of the satellite entering the target receiving range on the 2 nd or 3 rd day based on the latest and normal track instantaneous number received on the 3 rd day 2 ' calculating t 2 Difference t with 2 Absolute value ofTo DeltaT 2 And so on until the start time t of the satellite entering the target receiving range on the m-2 th day or the m-1 th day is calculated based on the latest and normal instantaneous number of orbits received on the m-2 th day m-2 Calculating the starting time t of the satellite entering the target receiving range on the m-2 th day or the m-1 th day based on the latest and normal instantaneous number of orbits received on the m-1 th day m-2 ' calculating t m-2 And t m-2 The absolute value of the difference' gives DeltaT m-2 Together to obtain DeltaT 1 To DeltaT m-2 M-2 differences in total.
When m is not greater than n, calculateAnd obtaining a standard time difference threshold value, wherein n is the revisit period of the satellite.
Specifically, m-2 differences obtained by the calculation are all from day 1 to day m-1, and the absolute values of the differences of the two starting times corresponding to one day in the two days are calculated sequentially based on the two latest and normal track instantaneous numbers received in each day, so that the average value of some differences in the m-2 differences can be taken as a standard time difference threshold of one day at intervals, the revisiting period of the satellite is the time interval of two adjacent observations of the satellite under the satellite passing through the same place, when m is not more than n, the obtained m-2 differences are smaller in number, so that the average value of the m-2 differences can be directly calculated as the standard time difference threshold of one day at intervals, and the product of the average value of the m-2 differences and m-k should be calculated as the standard time difference threshold because m and k intervals are not necessarily one day.
When m is greater than n, calculatingA standard time difference threshold is obtained.
Specifically, when m is greater than n, indicating that a revisit period has elapsed, referring to the revisit period n, selecting an absolute value of a difference value of each start time calculated based on the instantaneous root number of the track received in the last n days before the mth day, that is, calculating an average value from the mth-n difference value to the mth-2 difference value in the mth-2 difference values, as a standard time difference threshold value of one day, and calculating a product of the obtained average value and the m-k as the standard time difference threshold value.
According to the method, firstly, a standard time difference threshold value of one day at intervals is determined, then the product of the time difference threshold value and m-k is used as the standard time difference threshold value, and since the standard time difference threshold value of one day at intervals is calculated from the 1 st day to the m-1 st day, absolute values of differences of starting times of satellites entering a target receiving range on the previous day or the next day in two days are calculated sequentially based on the latest and normal two track instantaneous roots received on two continuous days, m-2 differences are obtained, average values of some differences are selected from the m-2 differences to be calculated, and time differences of two starting times corresponding to one day in two days are calculated based on the latest and normal track instantaneous roots received on one day in all 1 st to m-1 th days, so that the finally determined standard time difference threshold value is more standard.
Optionally, when m is greater than n, the product of the average value of the last n differences in the m-2 differences and m-k may be calculated to obtain a standard time difference threshold, and the number of the selected differences may be selected with reference to other standards in addition to the reference revisit period n.
Second kind:
and calculating the absolute value of the difference value of the starting time of the satellite entering the target receiving range on the previous day or the next day of two days based on the latest and normal instantaneous root numbers of the two tracks received on two continuous days from the 1 st day to the m-1 st day, so as to obtain m-2 difference values.
When m is not greater than n, calculateAnd obtaining an initial standard time difference threshold value, wherein n is the revisit period of the satellite.
When m is greater than n, calculatingAn initial standard time difference threshold is obtained.
And calculating the difference value between the maximum difference value and the minimum difference value in the m-2 difference values to obtain a compensation value.
Specifically, the calculated initial standard time difference threshold is a standard time difference threshold of one day interval, and since the initial standard time difference threshold is obtained by calculating an average value of absolute values of differences of all starting times, an upper limit error is caused, and in order to eliminate the upper limit error caused by the average value, a difference value between a maximum difference value and a minimum difference value in m-2 difference values is calculated, so as to obtain a compensation value.
And calculating the sum of the initial standard time difference threshold and the compensation value to obtain the standard time difference threshold.
Specifically, the sum of the initial standard time difference threshold and the compensation value is calculated, and the obtained standard time difference threshold is made to be the threshold with the upper limit error eliminated, and is more standard.
The standard time difference threshold finally determined in the embodiment of the application not only refers to all of the 1 st to m-1 th days, calculates the time difference of two starting times corresponding to one of the two days based on the two latest and normal track instantaneous roots received at intervals of one day, but also calculates the difference between the maximum difference and the minimum difference in the m-2 differences by taking the upper limit error caused by the calculation average into consideration, so as to obtain a compensation value, calculates the sum of the initial standard time difference threshold and the compensation value, so as to obtain a standard time difference threshold, and the finally determined standard time difference threshold is more standard.
Optionally, from day 1 to day m-1, calculating the absolute value of the difference value of the start time of the satellite entering the target receiving range on the previous day or the next day of the two days based on the latest and normal two track instantaneous numbers received on two continuous days in sequence, and after obtaining m-2 difference values, directly calculating the average value of the m-2 difference values to obtain a standard time difference threshold.
On the basis of the above embodiment, the present embodiment describes a process for determining whether the time difference is within a reasonable time range by referring to the preset standard time difference threshold, where the process may include:
judging whether the standard time difference threshold is not smaller than the time difference;
if yes, determining that the time difference is in a reasonable time range;
if not, determining that the time difference is not in a reasonable time range.
Alternatively, on the basis of the above embodiment, when m is greater than n, m-n is less than or equal to k < m.
Specifically, when m is greater than n, the absolute value of the difference value of each starting time calculated based on the instantaneous root number of the track received in the last n days before the mth day is selected, that is, the average value from the mth-n difference value to the mth-2 difference value in the mth-2 difference values is calculated, so that in order to make the determination more accurate, any day can be selected as k in the last n days before the mth day, that is, m-n is less than or equal to k < m.
In the embodiment of the application, when m is greater than n, the absolute value of the difference value of each starting time calculated based on the instantaneous root number of the track received in the last n days before the mth day is selected, that is, the average value from the mth-n difference value to the mth-2 difference value in the mth-2 difference values is calculated, so that m-n is less than or equal to k < m, that is, k is any one of the last n days before the mth day, so that the judgment is more accurate.
Alternatively, on the basis of the above embodiment, considering that the finally determined standard time difference threshold is calculated based on the absolute value of the difference between the start times of the satellites entering the target receiving range on the previous day or the next day of two days, which is sequentially calculated based on the latest and normal two instantaneous orbit numbers received on two consecutive days from day 1 to day m-1, the obtained m-2 differences are calculated, so k can be directly selected to be m-1, and k and m are separated by only one day, so that the determination is more accurate.
Optionally, the present embodiment finds that the instantaneous orbit root number includes six parameters, including a semi-long axis of orbit, an eccentricity of orbit, an inclination angle of orbit, an ascent and intersection point, an ascent and descent point angle, and a descent point angle, and in practical application, the difference of a plurality of different instantaneous orbit root numbers of the same satellite cannot be intuitively compared through the six parameters, and based on this, the embodiment of the present application provides a method for comparing the difference of a plurality of different instantaneous orbit root numbers of the same satellite, which may include:
firstly, acquiring a plurality of instantaneous orbit root numbers and parameters of corresponding ground receiving stations, which need to judge the difference, respectively calculating the starting time of the satellite entering the target receiving range of the ground receiving station on the same day based on each instantaneous orbit root number and parameters, obtaining a plurality of starting times, and comparing the differences of the instantaneous orbit root numbers by comparing the differences of the starting times corresponding to the instantaneous orbit root numbers.
In the embodiment of the application, the instantaneous track root number is normalized to be a time value, so that the difference of different instantaneous track root numbers can be judged by comparing the difference of the time values.
The following describes a satellite orbit parameter determination device provided in the embodiments of the present application, and the satellite orbit parameter determination device described below and the satellite orbit parameter determination device described above may be referred to correspondingly to each other.
First, referring to fig. 3, a satellite orbit parameter determination device will be described, and as shown in fig. 3, the satellite orbit parameter determination device may include:
a parameter obtaining unit 10, configured to obtain parameters of a ground receiving station corresponding to a satellite to be determined;
a first start time calculating unit 20, configured to calculate, when receiving a target instantaneous number of orbits corresponding to the satellite, a first start time of the satellite entering a target receiving range of the ground receiving station on a target circle number on an x-th day based on the target instantaneous number of orbits and the parameter, where a number of days when the target instantaneous number of orbits corresponding to the satellite is received for the first time is 1-th day, x is less than or equal to m, and m is a number of days when the target instantaneous number of orbits is received;
a second start time calculation unit 30, configured to calculate a second start time of the satellite entering the target receiving range on the target circle number on the x-th day based on the latest track instantaneous root number among the normal track instantaneous root numbers received on the k-th day and the parameter;
a time difference calculating unit 40, configured to calculate an absolute value of a difference between the first start time and the second start time, to obtain a time difference;
a time difference judging unit 50 for judging whether the time difference is within a reasonable time range by referring to a preset standard time difference threshold;
if yes, the following step of the target track instantaneous root judgment unit 60 is executed;
a determination unit 60 for determining that the instantaneous root number of the target track is normal.
Alternatively, x=k < m;
the satellite orbit parameter determination device may further include:
a first difference calculating unit, configured to calculate, from day 1 to day m-1, absolute values of differences of start times of the satellite entering the target receiving range on a previous day or a subsequent day of two consecutive days in order based on the latest and normal two track instantaneous numbers received on the two consecutive days, to obtain m-2 differences;
the first standard time difference threshold calculating unit is used for calculating the product of the average value of the m-2 difference values and m-k to obtain a standard time difference threshold when the m is not more than n, wherein n is the revisit period of the satellite;
and the second standard time difference threshold calculating unit is used for calculating the product of the m-n difference value in the m-2 difference values to the average value of the m-2 difference values and m-k to obtain a standard time difference threshold when the m is larger than the n.
Alternatively, x=k < m;
the satellite orbit parameter determination device may further include:
a second difference calculating unit, configured to calculate, from day 1 to day m-1, absolute values of differences of start times of the satellites entering the target receiving range on a previous day or a subsequent day of two consecutive days in order based on the latest and normal two track instantaneous numbers received on the two consecutive days, to obtain m-2 differences;
the first initial standard time difference threshold calculating unit is used for calculating the product of the average value of the m-2 difference values and m-k to obtain an initial standard time difference threshold when the m is not more than n, wherein n is the revisit period of the satellite;
the second initial standard time difference threshold calculating unit is used for calculating the product of the m-n difference value in the m-2 difference values to the average value of the m-2 difference values and m-k when the m is larger than the n, so as to obtain an initial standard time difference threshold;
the compensation value calculation unit is used for calculating the difference value between the maximum difference value and the minimum difference value in the m-2 difference values to obtain a compensation value;
and the third standard time difference threshold calculating unit is used for calculating the sum of the initial standard time difference threshold and the compensation value to obtain the standard time difference threshold.
Optionally, the process of determining whether the time difference is within a reasonable time range by the time difference determining unit referring to a preset standard time difference threshold may include:
judging whether the standard time difference threshold is not smaller than the time difference;
if yes, determining that the time difference is in a reasonable time range;
if not, determining that the time difference is not in a reasonable time range.
Alternatively, when m is greater than n, m-n is less than or equal to k < m.
Optionally, the parameters may include: coordinates of the receiving antenna, elevation range and azimuth range.
Optionally, the satellite orbit parameter determining device may further include:
and the reporting unit is used for reporting the instantaneous root number of the target track to the data receiving and processing system.
The satellite orbit parameter determination device provided by the embodiment of the application can be applied to satellite orbit parameter determination equipment. Fig. 4 shows a block diagram of a hardware structure of the satellite orbit parameter determination device, and referring to fig. 4, the hardware structure of the satellite orbit parameter determination device may include: at least one processor 1, at least one communication interface 2, at least one memory 3 and at least one communication bus 4;
in the embodiment of the application, the number of the processor 1, the communication interface 2, the memory 3 and the communication bus 4 is at least one, and the processor 1, the communication interface 2 and the memory 3 complete communication with each other through the communication bus 4;
processor 1 may be a central processing unit CPU, or a specific integrated circuit ASIC (Application Specific Integrated Circuit), or one or more integrated circuits configured to implement embodiments of the present invention, etc.;
the memory 3 may comprise a high-speed RAM memory, and may further comprise a non-volatile memory (non-volatile memory) or the like, such as at least one magnetic disk memory;
wherein the memory stores a program, the processor is operable to invoke the program stored in the memory, the program operable to: and realizing each processing flow in the satellite orbit parameter judgment scheme.
The embodiment of the application also provides a storage medium, which may store a program adapted to be executed by a processor, the program being configured to: and realizing each processing flow in the satellite orbit parameter judgment scheme.
Finally, it is further noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A satellite orbit parameter determination method, comprising:
acquiring parameters of a ground receiving station corresponding to a satellite to be judged;
when the target instantaneous orbit root number corresponding to the satellite is received, calculating a first starting time of the satellite entering a target receiving range of the ground receiving station on the target circle number on the x th day based on the target instantaneous orbit root number and the parameter, wherein the number of days for receiving the target instantaneous orbit root number corresponding to the satellite for the first time is 1 st day, x is less than or equal to m, and m is the number of days for receiving the target instantaneous orbit root number;
calculating a second starting time of the satellite entering the target receiving range on the x-th day on the basis of the latest track instantaneous root number in the normal track instantaneous root number received on the k-th day and the parameters, wherein k is less than or equal to m;
calculating the absolute value of the difference value between the first starting time and the second starting time to obtain a time difference;
judging whether the time difference is in a reasonable time range or not by referring to a preset standard time difference threshold;
if yes, judging that the instantaneous root number of the target track is normal.
2. The method according to claim 1, characterized in that x = k < m;
the determining process of the standard time difference threshold comprises the following steps:
calculating absolute values of differences of starting times of the satellites entering the target receiving range on the previous day or the next day of two days sequentially based on the latest and normal two track instantaneous numbers received on two continuous days from the 1 st day to the m-1 st day to obtain m-2 differences;
when m is not greater than n, calculating the product of the average value of the m-2 differences and m-k to obtain a standard time difference threshold value, wherein n is the revisit period of the satellite;
and when m is larger than n, calculating the product of the m-n difference value in the m-2 difference values to the average value of the m-2 difference values and m-k to obtain a standard time difference threshold.
3. The method according to claim 1, characterized in that x = k < m;
the determining process of the standard time difference threshold comprises the following steps:
calculating absolute values of differences of starting times of the satellites entering the target receiving range on the previous day or the next day of two days sequentially based on the latest and normal two track instantaneous numbers received on two continuous days from the 1 st day to the m-1 st day to obtain m-2 differences;
when m is not greater than n, calculating the product of the average value of the m-2 differences and m-k to obtain an initial standard time difference threshold value, wherein n is the revisit period of the satellite;
when m is larger than n, calculating the product of the m-n difference value in the m-2 difference values to the average value of the m-2 difference values and m-k to obtain an initial standard time difference threshold;
calculating the difference value between the maximum difference value and the minimum difference value in the m-2 difference values to obtain a compensation value;
and calculating the sum of the initial standard time difference threshold and the compensation value to obtain the standard time difference threshold.
4. A method according to claim 2 or 3, wherein said determining whether said time difference is within a reasonable time frame with reference to a preset standard time difference threshold comprises:
judging whether the standard time difference threshold is not smaller than the time difference;
if yes, determining that the time difference is in a reasonable time range;
if not, determining that the time difference is not in a reasonable time range.
5. A method according to claim 2 or 3, wherein when m is greater than n, m-n is less than or equal to k < m.
6. The method of claim 1, wherein the parameters include: coordinates of the receiving antenna, elevation range and azimuth range.
7. The method of claim 1, 2, 3 or 6, further comprising, after determining that the target track transient root number is normal:
and reporting the instantaneous number of the target track to a data receiving and processing system.
8. A satellite orbit parameter determination device, comprising:
the parameter acquisition unit is used for acquiring parameters of a ground receiving station corresponding to the satellite to be judged;
the first starting time calculation unit is used for calculating the first starting time of the satellite entering the target receiving range of the ground receiving station on the target circle number on the x th day based on the target track instantaneous root number and the parameter when the target track instantaneous root number corresponding to the satellite is received, wherein the number of days for receiving the track instantaneous root number corresponding to the satellite for the first time is 1 st day, x is less than or equal to m, and m is the number of days for receiving the target track instantaneous root number;
a second start time calculation unit, configured to calculate a second start time of the satellite entering the target receiving range on the target circle number on the x-th day based on the latest track instantaneous root number among the normal track instantaneous root numbers received on the k-th day and the parameter, where k is less than or equal to m;
a time difference calculating unit, configured to calculate an absolute value of a difference between the first start time and the second start time, to obtain a time difference;
the time difference judging unit is used for referring to a preset standard time difference threshold value to judge whether the time difference is in a reasonable time range or not;
if yes, executing the following steps of a target track instantaneous root number judging unit;
and the judging normal unit is used for judging that the instantaneous root number of the target track is normal.
9. A satellite orbit parameter determination device, comprising a memory and a processor;
the memory is used for storing programs;
the processor for executing the program to implement the steps of the satellite orbit parameter determination method according to any one of claims 1 to 7.
10. A readable storage medium having stored thereon a computer program, which, when executed by a processor, implements the steps of the satellite orbit parameter determination method according to any one of claims 1-7.
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