CN115828035A - On-orbit fitting estimation method for sunlight pressure interference moment of geostationary orbit satellite - Google Patents
On-orbit fitting estimation method for sunlight pressure interference moment of geostationary orbit satellite Download PDFInfo
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Abstract
The invention relates to the technical field of spacecraft control, and provides an on-orbit fitting estimation method for a solar light pressure interference moment of a geostationary orbit satellite, which comprises the following steps: generating an expression formula of the sunlight pressure interference moment by utilizing a Fourier series form; fitting by utilizing the sampled momentum wheel angular momentum data to obtain a fitting coefficient in a corresponding expression formula of each fitting time period; determining the fitting time corresponding to the satellite at the forecast position based on the fitting starting time corresponding to different fitting time periods in the sunlight pressure period and the fitting starting position of the satellite; calculating the julian annual difference between the forecast time and the fitting time; determining a target fitting time period matched with the forecast time according to the julian annual difference and each fitting time period divided in the sunlight pressure period; and calculating the sunlight pressure interference moment at the forecast time by using the fitting coefficient of the target fitting time period. According to the scheme, the sunlight pressure interference moment at the forecast time can be fitted and estimated in orbit, and the requirement of satellite in-orbit control precision can be met.
Description
Technical Field
The embodiment of the invention relates to the technical field of spacecraft control, in particular to an on-orbit fitting estimation method for a solar light pressure interference moment of a geostationary orbit satellite.
Background
The satellite needs to use electric propulsion to complete a position keeping and angular momentum unloading task on a static orbit, in order to realize the electric propulsion angular momentum unloading task, a disturbance moment generated by electric propulsion ignition needs to be accurately estimated, an estimated measurement source is the angular momentum change of a momentum wheel, and the influence of the disturbance moment needs to be deducted from the angular momentum change. For a stationary orbit satellite, the disturbance torque is mainly the sunlight pressure disturbance torque, so the sunlight pressure disturbance torque needs to be estimated accurately and in real time on the satellite.
Because the sunlight pressure disturbance moment model is influenced by a plurality of factors, the traditional sunlight pressure disturbance moment estimation method based on accurate modeling has the problem of overlarge real-time estimation calculation amount, the precision is not ideal, and the application requirements on the satellite are difficult to meet.
Disclosure of Invention
The embodiment of the invention provides an on-orbit fitting estimation method for the sunlight pressure interference moment of a geostationary orbit satellite, which can be used for obtaining the sunlight pressure interference moment at the forecast time through on-orbit fitting and can meet the requirement on the on-orbit estimation precision of the satellite.
In a first aspect, an embodiment of the present invention provides an on-orbit fitting estimation method for a solar light pressure disturbance moment of a geostationary orbit satellite, including:
generating an expression formula of the sunlight pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients;
the solar light pressure cycle is divided into a plurality of fitting periods, and for each fitting period: based on momentum wheel angular momentum data obtained by sampling in the fitting time period, converting the momentum wheel angular momentum data into an equivalent measurement value of sunlight pressure interference moment by taking the initial time of the sunlight pressure period as the fitting initial time, and fitting according to the expression formula to obtain a fitting coefficient of the fitting time period;
determining the fitting time corresponding to the satellite at the forecast position based on the fitting starting time corresponding to different fitting time periods in the sunlight pressure period and the fitting starting position of the satellite;
calculating the julian year difference between the forecast time and the fitting time, and determining a target fitting time period matched with the forecast time according to the julian year difference and each fitting time period divided in the sunlight pressure period;
and calculating the sunlight pressure interference moment at the forecast time by using the fitting coefficient of the sunlight pressure interference moment in the target fitting time period.
In a second aspect, an embodiment of the present invention further provides an in-orbit fitting estimation apparatus for a solar light pressure disturbance moment of a geostationary orbit satellite, including:
the fitting coefficient acquisition unit is used for generating an expression formula of the sunlight pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients; the solar light pressure cycle is divided into a plurality of fitting periods, and for each fitting period: based on momentum wheel angular momentum data obtained by sampling in the fitting time period, converting the momentum wheel angular momentum data into an equivalent measurement value of sunlight pressure interference moment by taking the initial time of the sunlight pressure period as the fitting initial time, and fitting according to the expression formula to obtain a fitting coefficient of the fitting time period;
the first determining unit is used for determining the fitting time corresponding to the satellite at the forecast position based on the fitting starting time corresponding to different fitting time periods in the sunlight pressure period and the fitting starting position of the satellite;
a first calculating unit, configured to calculate a julian year difference between a forecast time and the fitting time;
the second determining unit is used for determining a target fitting time period matched with a forecast time according to the julian annual difference and each fitting time period divided in the sunlight pressure period;
and the second calculation unit is used for calculating the sunlight pressure interference moment at the forecast time by using the fitting coefficient of the sunlight pressure interference moment in the target fitting time period.
In a third aspect, an embodiment of the present invention further provides an electronic device, which includes a memory and a processor, where the memory stores a computer program, and the processor executes the computer program to implement the method according to any embodiment of this specification.
In a fourth aspect, the present invention further provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed in a computer, the computer program causes the computer to execute the method described in any embodiment of the present specification.
The embodiment of the invention provides an on-orbit fitting estimation method for a sunlight pressure interference moment of a geostationary orbit satellite, which comprises the steps of generating an expression formula of the sunlight pressure interference moment by utilizing a Fourier series form, fitting to obtain fitting coefficients of the sunlight pressure interference moment in different fitting time periods based on momentum wheel angular momentum data obtained by sampling, storing the fitting coefficients in different fitting time periods in the satellite, determining a target fitting time period matched with a forecast time based on a Joule annual difference by calculating the Joule annual difference after the conversion is finished as the result of the change of the satellite position, namely changing the fitting initial position in the fitting process to the forecast position when the satellite is at an orbit fitting forecast position, and obtaining the sunlight pressure interference moment at the forecast position by using the fitting coefficient corresponding to the target fitting time period as a coefficient used for calculating the sunlight pressure interference moment. Therefore, the method can be matched with the actual fitting position of the satellite, the on-orbit calculation of the sunlight pressure interference torque is carried out, the calculated amount is small, and the on-orbit estimation accuracy of the sunlight pressure interference torque of the satellite can be met.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a flowchart of an in-orbit fitting estimation method for a solar light pressure disturbance moment of a geostationary orbit satellite according to an embodiment of the present invention;
fig. 2 is a hardware architecture diagram of an electronic device according to an embodiment of the present invention;
fig. 3 is a structural diagram of an in-orbit fitting estimation apparatus for a solar light pressure disturbance moment of a geostationary orbit satellite according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer and more complete, the technical solutions in the embodiments of the present invention will be described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention, and based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the scope of the present invention.
Referring to fig. 1, an embodiment of the present invention provides an on-orbit fitting estimation method for a solar light pressure disturbance moment of a geostationary orbit satellite, including:
104, determining the fitting time corresponding to the satellite at the forecast position based on the fitting starting time corresponding to different fitting time periods in the sunlight pressure cycle and the fitting starting position of the satellite;
and step 108, calculating the sunlight pressure interference moment at the forecast time by using the fitting coefficient of the sunlight pressure interference moment in the target fitting time period.
In the embodiment of the invention, an expression formula of sunlight pressure interference moment is generated by utilizing a Fourier series form, fitting coefficients of the sunlight pressure interference moment in different fitting time periods are obtained based on momentum wheel angular momentum data obtained by sampling in a fitting mode, the fitting coefficients in different fitting time periods are stored in a satellite, when the sunlight pressure interference moment at an orbit fitting forecasting position of the satellite is changed, the position of the satellite is changed, namely the fitting initial position in the fitting process is changed to the forecasting position, so that the fitting time needs to be converted, after the conversion is completed, a target fitting time period matched with the forecasting time is determined based on the julian annual difference by calculating the julian annual difference, and the fitting coefficient corresponding to the target fitting time period is used as a coefficient for calculating the sunlight pressure interference moment to obtain the sunlight pressure interference moment at the forecasting time under the forecasting position. Therefore, the method can be matched with the actual fitting position of the satellite, the on-orbit calculation of the sunlight pressure interference torque is carried out, the calculated amount is small, and the on-orbit estimation accuracy of the sunlight pressure interference torque of the satellite can be met.
The manner in which the various steps shown in fig. 1 are performed is described below.
First, step 100 and step 102 are addressed.
In the embodiment of the invention, the expression formula for generating the sunlight pressure interference moment by utilizing the Fourier series form can be as follows:
wherein ,T d in order to disturb the moment by the sunlight pressure,Nin order of the Fourier series,Tin order to be the solar light pressure period,Tin the same way as the period of the track,tis the time relative to the start time of the fit,
，
，
the fitting coefficients correspond to a constant term and a period term, respectively.
In step 102, since the period of revolution of the earth around the sun is one year, the complete solar light pressure period of the satellite on the earth's stationary orbit is also one year. For example, 1 month 1 to 12 months 31 days, or 2 months 1 to 1 month 31 days of the second year.
In addition, since the evolution law of the sunlight pressure disturbance moment in the whole sunlight pressure period is different from the influence of the sunlight pressure on the satellite, in order to improve the accuracy of the on-orbit calculation result, the sunlight pressure period may be divided into a plurality of fitting periods, for example, into 4 fitting periods, 12 fitting periods, and the like. Taking the sunlight pressure cycle from 1 month and 1 day to 12 months and 31 days as an example, the sunlight pressure cycle can be divided into 4 fitting time periods, namely 1 month and 1 day to 3 months and 31 days, 4 months and 1 day to 6 months and 30 days, 7 months and 1 day to 9 months and 30 days, and 10 months and 1 day to 12 months and 31 days.
In order to ensure the accuracy of the calculation result of the sunlight pressure disturbance moment, the momentum wheel angular momentum data needs to be sampled for each fitting time period. To reduce computational effort, the sampling may be done continuously for a sampling period or a plurality of sampling periods within the fitting period, without sampling the entire fitting period.
The sampling mode of the momentum wheel angular momentum data can comprise two modes: the first method is that under the condition that extra disturbance torque such as ignition work of an electric thruster does not exist, the actual measurement data of the momentum wheel angular momentum on the orbit is obtained; and the second is estimated data obtained by calculation by utilizing a ground calculation model simulating an on-orbit equivalent state.
Because each momentum wheel angular momentum data corresponds to a time and a position, and the sunlight pressure interference moment can be calculated by utilizing the momentum wheel angular momentum data, the momentum wheel angular momentum data sampled in each fitting time period can be converted into an equivalent measurement value of the sunlight pressure interference moment, and then fitting is carried out according to the expression formula to obtain the fitting coefficient corresponding to each fitting time period respectively
，
，
。
It should be noted that the fitting start time in the fitting process is the start time of the sunlight pressure cycle, for example, the sunlight pressure cycle is 1 month and 1 day to 3 months and 31 days, and then the 1 month and 1 day and 0 point may be used as the start time.
It should be noted that, the steps 100-102 may be performed on the ground and then the fitting coefficients of each time period are stored in the satellite, or the satellite is obtained by performing an in-orbit fitting based on the momentum wheel angular momentum data.
Then, in step 104, based on the fitting start time corresponding to different fitting time periods in the sunlight pressure cycle and the fitting start position of the satellite, the fitting time corresponding to the satellite at the forecast position is determined.
Since the association between the fitting time and the orbit position depends on the position of the satellite, when the position of the satellite changes, a new fitting time needs to be converted according to the time angle of the new position relative to the original position.
In an embodiment of the present invention, the fitting time of the satellite at the forecast position can be calculated by the following formula:
wherein tsrp is the cumulative seconds of the fitting moment relative to the satellite time reference, tsrp0 is the cumulative seconds of the fitting starting moment relative to the satellite time reference, SKLon0 is the fitting starting position of the satellite, and SKLon is the predicted position of the satellite;
for example, tsrp0=473155281s, sklon0=115 °, SKLon =125 °, the cumulative seconds tsrp of the fitting time of the solar light pressure disturbance moment after considering the position change with respect to the star time reference is:
next, in step 106, julian year difference between the forecast time and the fitting time is calculated, and a target fitting time period matched with the forecast time is determined according to the julian year difference and each fitting time period divided in the solar light pressure cycle.
In the embodiment of the invention, the forecast time can be the current time or a certain future time.
Specifically, the calculation of julian annual difference between the forecast time and the fitting time may include the following steps S1-S2:
s1, calculating the julian years of the forecast time and the fitting time relative to julian day reference respectively;
in the embodiment of the invention, 0 minute and 0 second at 2000 of Greenwich mean time, 1 of month, 1 of day, and 12 of day are taken as the julian day reference, and then the julian year of the forecast time relative to the julian day reference can be calculated by using the following formula:
d_jul_ta= ta/86400+ d_jul0
J1= floor(d_jul_ta +2451546 )
d _ jul _ ta is a julian day of which the forecast time is relative to a julian day reference, ta is an accumulated second number of which the forecast time is relative to a satellite time reference, d _ jul0 is a julian day of which the satellite time reference is relative to a julian day reference, floor (x) is an integer which is taken downwards from x, J1, N1 and L1 are intermediate parameters, and Y _ jul _ ta is a julian year of which the forecast time is relative to the julian day reference;
further, julian years for the fitting moments relative to julian day benchmarks can be calculated using the following formula:
d_jul_srp= tsrp/86400+ d_jul0
J2= floor(d_jul_srp +2451546 )
wherein d _ jul _ srp is the julian day of the fitting time relative to the julian day reference, J2, N2, and L2 are intermediate parameters, and Y _ jul _ srp is the julian year of the fitting time relative to the julian day reference.
And S2, taking the difference value of the two julian years obtained by calculation as the julian year difference between the forecast time and the fitting time.
According to the two julian years Y _ jul _ ta and Y _ jul _ srp obtained in the above step S1, the difference between Y _ jul _ ta and Y _ jul _ srp can be used as the julian year difference.
For example, if the star-time reference is set to 0 minutes and 0 seconds at 1 month, 1 day, 0, 2006, then the julian day for the star-time reference relative to the julian day reference is d _ jul0=2191.5, thereby resulting in tsrp =473157681s, then the julian day d _ jul _ srp and julian year Y _ jul _ srp for the tsrp relative to the julian day reference are:
d_jul_srp =7667.862
J2 =2459213
N2 =69
L2=7608
Y_jul_srp =20.8333
and if the cumulative seconds ta =482661681s of the forecast time relative to the star time reference, the julian day d _ jul _ ta and the julian year Y _ jul _ ta of the forecast time relative to the julian day reference are:
d_jul_ta =7777.862
J1 =2459323
N1=69
L1 =7718
Y_jul_ta =21.1335。
in the embodiment of the present invention, in order to determine the target fitting coefficient, a target fitting time period matched with the forecast time needs to be determined first, and specifically, a jth fitting time period may be determined as the target fitting time period by using the following formula:
wherein ceil (x) is an upward integer of x, and numSRPdata is the total number of periods obtained after the solar light pressure cycle is divided into each fitting period; y _ jul _ ta is the julian year whose forecast time is relative to the julian day reference, and Y _ jul _ srp is the julian year whose fitting time is relative to the julian day reference.
Continuing with the above example of Y _ jul _ srp =20.8333 and Y _ jul _ ta =21.1335, j =2 may be calculated, and then the fitting coefficient corresponding to the 2 nd fitting period may be selected.
Finally, in step 108, the sunlight pressure disturbance moment at the forecast time is calculated by using the fitting coefficient of the sunlight pressure disturbance moment in the target fitting time period.
When the fitting coefficient of the jth fitting period is selected, it is possibleCalculating the sunlight pressure interference moment at the forecast time at the forecast position based on Fourier series expression
：
wherein ,
is the fitting coefficient for the jth fitting period.
In the embodiment of the invention, the fitting coefficient is obtained by driving the momentum wheel angular momentum data, and the solar light pressure interference torque on-orbit fitting calculation is suitable for light pressure evolution laws at different positions and different time periods according to the converted fitting time of different positions of the satellite. The method can be used for on-orbit calculation of the sunlight pressure interference moment and on-orbit calculation of the sunlight pressure perturbation force, and is widely suitable for satellites with the requirements of precise orbit determination or high-precision interference moment estimation in a static orbit.
As shown in fig. 2 and fig. 3, an in-orbit fitting estimation apparatus for a solar light pressure disturbance moment of a geostationary orbit satellite is provided in an embodiment of the present invention. The device embodiments may be implemented by software, or by hardware, or by a combination of hardware and software. From a hardware aspect, as shown in fig. 2, for a hardware architecture diagram of an electronic device in which an on-orbit fitting apparatus for a solar light pressure disturbance moment of a geostationary orbit satellite according to an embodiment of the present invention is located, in addition to the processor, the memory, the network interface, and the nonvolatile memory shown in fig. 2, the electronic device in which the apparatus is located in the embodiment may generally include other hardware, such as a forwarding chip responsible for processing a message, and the like. Taking a software implementation as an example, as shown in fig. 3, as a logical device, a CPU of the electronic device reads a corresponding computer program in the non-volatile memory into the memory for running. The on-orbit fitting estimation device for the sunlight pressure interference moment of the geostationary orbit satellite provided by the embodiment comprises:
a fitting coefficient obtaining unit 301, configured to generate an expression formula of the sunlight pressure disturbance moment by using a fourier series form; the expression formula comprises a plurality of fitting coefficients; the solar light pressure cycle is divided into a plurality of fitting periods, and for each fitting period: based on momentum wheel angular momentum data obtained by sampling in the fitting time period, converting the momentum wheel angular momentum data into an equivalent measurement value of sunlight pressure interference moment by taking the initial time of the sunlight pressure period as the fitting initial time, and fitting according to the expression formula to obtain a fitting coefficient of the fitting time period;
a first determining unit 302, configured to determine a fitting time corresponding to the satellite at the forecast position based on fitting start times corresponding to different fitting time periods in the sunlight pressure cycle and a fitting start position of the satellite;
a first calculating unit 303, configured to calculate julian year differences between the forecast time and the fitting time;
a second determining unit 304, configured to determine a target fitting time period matched with a forecast time according to the julian annual difference and each fitting time period divided in the solar light pressure cycle;
a second calculating unit 305, configured to calculate the sunlight pressure disturbance moment at the forecast time by using the fitting coefficient of the sunlight pressure disturbance moment in the target fitting time period.
In one embodiment of the present invention, the expression formula is:
wherein ,T d in order to disturb the moment by the sunlight pressure,Nin order of the Fourier series,Tin order to be the solar light pressure period,Tin the same way as the track period,tis the time relative to the start time of the fit,
，
，
are fitting coefficients.
In an embodiment of the present invention, the first determining unit is specifically configured to calculate a fitting time corresponding to the satellite at the forecasted position by using the following formula:
wherein tsrp is the cumulative seconds of the fitting time relative to the satellite-time reference, tsrp0 is the cumulative seconds of the fitting starting time relative to the satellite-time reference, SKLon0 is the fitting starting position of the satellite, and SKLon is the predicted position of the satellite.
In an embodiment of the present invention, the first calculating unit is specifically configured to calculate julian years of forecast time and the fitting time relative to julian day references, respectively; and taking the difference value of the two julian years obtained by calculation as the julian year difference between the forecast time and the fitting time.
In an embodiment of the present invention, the second determining unit is specifically configured to determine a jth fitting period as the target fitting period by using the following formula:
wherein ceil (x) is an upward integer of x, and numSRPdata is the total number of fitting periods obtained after the solar light pressure cycle is divided into the fitting periods; y _ jul _ ta is the julian year of which the forecast time is relative to the julian day reference, and Y _ jul _ srp is the julian year of which the fitting time is relative to the julian day reference.
It can be understood that the illustrated structure of the embodiment of the invention does not constitute a specific limitation on the in-orbit fitting device for the solar light pressure disturbance moment of the geostationary orbit satellite. In other embodiments of the invention, an in-orbit fitting device for the solar light pressure disturbance moment of the geostationary orbit satellite can comprise more or less components than those shown, or combine some components, or split some components, or arrange different components. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.
Because the content of information interaction, execution process, and the like among the modules in the device is based on the same concept as the method embodiment of the present invention, specific content can be referred to the description in the method embodiment of the present invention, and is not described herein again.
The embodiment of the invention also provides electronic equipment which comprises a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to realize the on-orbit fitting estimation method of the solar light pressure interference moment of the geostationary orbit satellite in any embodiment of the invention.
Embodiments of the present invention further provide a computer-readable storage medium, on which a computer program is stored, where the computer program, when executed by a processor, causes the processor to execute an in-orbit fitting estimation method for a geostationary orbit satellite sunlight pressure disturbance moment in any of the embodiments of the present invention.
Specifically, a system or an apparatus equipped with a storage medium on which software program codes that realize the functions of any of the embodiments described above are stored may be provided, and a computer (or a CPU or MPU) of the system or the apparatus is caused to read out and execute the program codes stored in the storage medium.
In this case, the program code itself read from the storage medium can realize the functions of any of the above-described embodiments, and thus the program code and the storage medium storing the program code constitute a part of the present invention.
Examples of the storage medium for supplying the program code include a floppy disk, a hard disk, a magneto-optical disk, an optical disk (e.g., CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD + RW), a magnetic tape, a nonvolatile memory card, and a ROM. Alternatively, the program code may be downloaded from a server computer via a communications network.
Further, it should be clear that the functions of any one of the above-described embodiments may be implemented not only by executing the program code read out by the computer, but also by causing an operating system or the like operating on the computer to perform a part or all of the actual operations based on instructions of the program code.
Further, it is to be understood that the program code read out from the storage medium is written to a memory provided in an expansion board inserted into the computer or to a memory provided in an expansion module connected to the computer, and then a CPU or the like mounted on the expansion board or the expansion module is caused to perform part or all of the actual operations based on instructions of the program code, thereby realizing the functions of any of the embodiments described above.
It is noted that, herein, relational terms such as first and second, and the like may be 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. Also, 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 of 8230" does not exclude the presence of additional like elements in a process, method, article, or apparatus comprising the element.
Those of ordinary skill in the art will understand that: all or part of the steps for realizing the method embodiments can be completed by hardware related to program instructions, the program can be stored in a computer readable storage medium, and the program executes the steps comprising the method embodiments when executed; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. An on-orbit fitting estimation method for a sunlight pressure disturbance moment of a stationary orbit satellite is characterized by comprising the following steps:
generating an expression formula of the sunlight pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients;
the solar light pressure cycle is divided into a plurality of fitting periods, and for each fitting period: based on momentum wheel angular momentum data obtained by sampling in the fitting time period, converting the momentum wheel angular momentum data into an equivalent measurement value of sunlight pressure interference moment by taking the initial time of the sunlight pressure period as the fitting initial time, and fitting according to the expression formula to obtain a fitting coefficient of the fitting time period;
determining the fitting time corresponding to the satellite at the forecast position based on the fitting starting time corresponding to different fitting time periods in the sunlight pressure period and the fitting starting position of the satellite;
calculating the julian year difference between the forecast time and the fitting time, and determining a target fitting time period matched with the forecast time according to the julian year difference and each fitting time period divided in the sunlight pressure period;
and calculating the sunlight pressure interference moment at the forecast time by using the fitting coefficient of the sunlight pressure interference moment in the target fitting time period.
2. The method of claim 1, wherein the expression formula is:
wherein ,T d in order to disturb the moment by the sunlight pressure,Nin order of the Fourier series,Tin order to be the solar light pressure period,Tin the same way as the period of the track,tis the time relative to the start time of the fit,
，
，
are fitting coefficients.
3. The method of claim 1, wherein determining the fitting time corresponding to the satellite at the forecast position based on the fitting start time corresponding to the different fitting time periods in the solar light pressure cycle and the fitting start position of the satellite comprises:
calculating the corresponding fitting time of the satellite at the forecast position by using the following formula:
wherein tsrp is the cumulative seconds of the fitting time relative to the satellite time reference, tsrp0 is the cumulative seconds of the fitting starting time relative to the satellite time reference, SKLon0 is the fitting starting position of the satellite, and SKLon is the predicted position of the satellite.
4. The method of claim 3, wherein calculating the julian year difference between the forecast time and the fit time comprises:
calculating the julian years of the forecast time and the fitting time relative to julian day reference respectively;
and taking the difference value of the two julian years obtained by calculation as the julian year difference between the forecast time and the fitting time.
5. The method of claim 3, wherein determining a target fitting time period matched with a forecast time according to the julian year difference and each fitting time period divided in the solar light pressure cycle comprises:
determining the jth fitting period as the target fitting period using the following formula:
wherein ceil (x) is an upward integer of x, and numSRPdata is the total number of fitting periods obtained after the solar light pressure cycle is divided into the fitting periods; y _ jul _ ta is the julian year whose forecast time is relative to the julian day reference, and Y _ jul _ srp is the julian year whose fitting time is relative to the julian day reference.
6. An on-orbit fitting estimation device for a sunlight pressure disturbance moment of a geostationary orbit satellite is characterized by comprising the following components:
the fitting coefficient acquisition unit is used for generating an expression formula of the sunlight pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients; the solar light pressure cycle is divided into a plurality of fitting periods, and for each fitting period: based on momentum wheel angular momentum data obtained by sampling in the fitting time period, converting the momentum wheel angular momentum data into an equivalent measurement value of sunlight pressure interference moment by taking the initial time of the sunlight pressure period as the fitting initial time, and fitting according to the expression formula to obtain a fitting coefficient of the fitting time period;
the first determining unit is used for determining the fitting time corresponding to the satellite at the forecast position based on the fitting starting time corresponding to different fitting time periods in the sunlight pressure period and the fitting starting position of the satellite;
the first calculating unit is used for calculating the julian year difference between the forecast time and the fitting time;
the second determining unit is used for determining a target fitting time period matched with a forecast time according to the julian annual difference and each fitting time period divided in the sunlight pressure period;
and the second calculation unit is used for calculating the sunlight pressure interference moment at the forecast time by using the fitting coefficient of the sunlight pressure interference moment in the target fitting time period.
7. The apparatus according to claim 6, wherein the first determining unit is specifically configured to:
calculating the corresponding fitting time of the satellite at the forecast position by using the following formula:
wherein tsrp is the cumulative seconds of the fitting time relative to the satellite-time reference, tsrp0 is the cumulative seconds of the fitting starting time relative to the satellite-time reference, SKLon0 is the fitting starting position of the satellite, and SKLon is the predicted position of the satellite.
8. The apparatus of claim 7,
the first calculating unit is specifically used for calculating the julian years of forecast time and the fitting time relative to julian day reference respectively; taking the difference value of the two julian years obtained by calculation as the julian year difference between the forecast time and the fitting time;
and/or the presence of a gas in the gas,
the second determining unit is specifically configured to determine the jth fitting period as the target fitting period by using the following formula:
wherein ceil (x) is an upward integer of x, and numSRPdata is the total number of fitting periods obtained after the solar light pressure cycle is divided into the fitting periods; y _ jul _ ta is the julian year whose forecast time is relative to the julian day reference, and Y _ jul _ srp is the julian year whose fitting time is relative to the julian day reference.
9. An electronic device comprising a memory having stored therein a computer program and a processor that, when executing the computer program, implements the method of any of claims 1-5.
10. A computer-readable storage medium, on which a computer program is stored which, when executed in a computer, causes the computer to carry out the method of any one of claims 1-5.
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