CN115828035B - On-orbit fitting estimation method for solar pressure interference moment of stationary orbit satellite - Google Patents
On-orbit fitting estimation method for solar pressure interference moment of stationary 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 solar voltage interference moment of a static orbit satellite, which comprises the following steps: generating an expression formula of solar light pressure interference moment by utilizing a Fourier series form; fitting by using the sampled momentum wheel angular momentum data to obtain fitting coefficients in the corresponding expression formula of each fitting period; determining fitting time corresponding to a predicted position of a satellite based on fitting starting time corresponding to different fitting time periods in a solar photovoltaic period and fitting starting positions of the satellite; calculating the slightly annual difference between the forecast time and the fitting time; determining a target fitting period matched with the forecasting time according to the slightly annual difference and each fitting period divided in the solar light pressure period; and calculating the solar voltage interference moment at the forecast moment by using the fitting coefficient of the target fitting period. According to the scheme, the solar light pressure interference moment at the forecast moment can be estimated through on-orbit fitting, and the requirement of satellite on-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 solar voltage interference moment of a static orbit satellite.
Background
The satellite needs to use electric propulsion to complete position maintenance and angular momentum unloading tasks on a static orbit, so that the electric propulsion angular momentum unloading tasks can be realized, the disturbance moment generated by electric propulsion ignition needs to be accurately estimated, the estimated measurement source is the angular momentum change of a momentum wheel, and the influence of the disturbance moment needs to be subtracted. For the stationary orbit satellite, the disturbance torque is mainly the solar pressure disturbance torque, so that the satellite needs to be able to estimate the solar pressure disturbance torque more accurately and in real time.
Because the solar light pressure disturbance moment model is influenced by a plurality of factors, the traditional solar light 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 on-board application requirement is difficult to meet.
Disclosure of Invention
The embodiment of the invention provides an on-orbit fitting estimation method for solar pressure disturbance moment of a stationary orbit satellite, which can obtain the solar pressure disturbance moment at a forecast moment by on-orbit fitting and can meet the requirement of satellite on-orbit estimation precision.
In a first aspect, an embodiment of the present invention provides an in-orbit fitting estimation method for solar voltage interference moment of a stationary orbit satellite, including:
generating an expression formula of solar light pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients;
the solar photovoltaic cycle is divided into a plurality of fitting periods, each fitting period being performed: based on the momentum wheel angular momentum data obtained by sampling in the fitting period, taking the starting time of the solar light pressure period as the fitting starting time, converting the momentum wheel angular momentum data into an equivalent measurement value of the solar light pressure interference moment, and fitting according to the expression formula to obtain a fitting coefficient of the fitting period;
determining fitting time corresponding to a predicted position of a satellite based on fitting starting time corresponding to different fitting time periods in a solar photovoltaic period and fitting starting positions of the satellite;
calculating the julian annual difference between the forecasting time and the fitting time, and determining a target fitting time period matched with the forecasting time according to the julian annual difference and each fitting time period divided in the solar light pressure period;
and calculating the solar voltage disturbance moment at the forecast moment by using the fitting coefficient of the solar voltage disturbance moment at the target fitting period.
In a second aspect, an embodiment of the present invention further provides an in-orbit fitting estimation device for solar voltage interference moment of a stationary orbit satellite, including:
the fitting coefficient acquisition unit is used for generating an expression formula of solar light pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients; the solar photovoltaic cycle is divided into a plurality of fitting periods, each fitting period being performed: based on the momentum wheel angular momentum data obtained by sampling in the fitting period, taking the starting time of the solar light pressure period as the fitting starting time, converting the momentum wheel angular momentum data into an equivalent measurement value of the solar light pressure interference moment, and fitting according to the expression formula to obtain a fitting coefficient of the fitting period;
the first determining unit is used for determining fitting time corresponding to the satellite at the forecast position based on fitting starting time corresponding to different fitting time periods in the solar photovoltaic period and the fitting starting position of the satellite;
the first calculation unit is used for calculating the julian annual difference between the forecast time and the fitting time;
the second determining unit is used for determining a target fitting period matched with the forecasting time according to the slightly annual difference and each fitting period divided in the solar light pressure period;
and the second calculation unit is used for calculating the solar voltage disturbance moment at the forecasting time by using the fitting coefficient of the solar voltage disturbance moment of the target fitting period.
In a third aspect, an embodiment of the present invention further provides an electronic device, including a memory and a processor, where the memory stores a computer program, and when the processor executes the computer program, the method described in any embodiment of the present specification is implemented.
In a fourth aspect, embodiments of the present invention also provide a computer-readable storage medium having stored thereon a computer program which, when executed in a computer, causes the computer to perform a method according to any of the embodiments of the present specification.
The embodiment of the invention provides an on-orbit fitting estimation method for solar pressure interference moment of a static orbit satellite, which utilizes an expression formula of solar pressure interference moment generated in a Fourier series form, obtains fitting coefficients of solar pressure interference moment of different fitting periods based on momentum wheel angular momentum data obtained by sampling, stores the fitting coefficients of different fitting periods in the satellite, and when the satellite is in orbit fitting for the solar pressure interference moment at a forecast position, the position of the satellite changes, namely, the fitting initial position changes to the forecast position when the satellite is in orbit fitting, so that conversion of fitting time is needed, after conversion is completed, a target fitting period matched with the forecast time is determined based on the Condition time by calculating the Condition time, and the fitting coefficient corresponding to the target fitting period is used as a coefficient used for calculating the solar pressure interference moment to obtain the solar pressure interference moment at the forecast time at the forecast position. Therefore, the scheme can be matched with the actual fitting position of the satellite, and the solar pressure interference moment is calculated on orbit, so that the calculated amount is small, and the on-orbit estimation precision of the solar pressure interference moment of the satellite can be met.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flowchart of an in-orbit fitting estimation method for solar voltage disturbance moment of a stationary 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 block diagram of an on-orbit fitting estimation device for solar voltage disturbance moment of a stationary orbit satellite according to an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present invention are within the scope of protection of the present invention.
Referring to fig. 1, an embodiment of the present invention provides an in-orbit fitting estimation method for solar voltage interference moment of a stationary orbit satellite, which includes:
and step 108, calculating the solar voltage disturbance moment at the forecast time by using the fitting coefficient of the solar voltage disturbance moment at the target fitting period.
In the embodiment of the invention, an expression formula of solar voltage interference moment is generated by utilizing a Fourier series form, fitting coefficients of solar voltage interference moment in different fitting periods are obtained based on sampled momentum wheel angular momentum data, the fitting coefficients of different fitting periods are stored in a satellite, when the satellite fits the solar voltage interference moment at a forecast position in orbit, the position of the satellite changes, namely, the fitting initial position changes to the forecast position when fitting, so that conversion of fitting time is needed, after conversion is completed, a target fitting period matched with the forecast time is determined based on the slightly-old, and the fitting coefficient corresponding to the target fitting period is used as a coefficient used for calculating the solar voltage interference moment to obtain the solar voltage interference moment at the forecast time at the forecast position. Therefore, the scheme can be matched with the actual fitting position of the satellite, and the solar pressure interference moment is calculated on orbit, so that the calculated amount is small, and the on-orbit estimation precision of the solar pressure interference moment of the satellite can be met.
The manner in which the individual steps shown in fig. 1 are performed is described below.
First, for steps 100 and 102.
In the embodiment of the invention, the expression formula for generating the solar light pressure interference moment by utilizing the Fourier series form can be as follows:
wherein ,T d as the interference moment of the sunlight pressure,Nin order to be a fourier series of orders,Tin the case of a solar light pressure cycle,Tas in the case of the track period,tin order to be time relative to the moment of start of the fitting,
，/>
，/>
for the fitting coefficients, constant terms and period terms are respectively corresponding.
In step 102, since the period of revolution of the earth around the sun is one year, the complete solar pressure period of the satellite in the earth's stationary orbit is also one year. For example, 1 month 1 day to 12 months 31 days, or 2 months 1 day to 1 month 31 days of the second year.
In addition, because the evolution rule of the solar voltage interference moment in the whole solar voltage period and the influence of the solar voltage on the satellite are different, in order to improve the accuracy of the on-orbit calculation result, the solar voltage period can be divided into a plurality of fitting time periods, such as 4 fitting time periods, 12 fitting time periods and the like. Taking the example of the solar light pressure period of 1 month 1 day to 12 months 31 days, the fitting period can be divided into 4 fitting periods of 1 month 1 day to 3 months 31 days, 4 months 1 day to 6 months 30 days, 7 months 1 day to 9 months 30 days, and 10 months 1 day to 12 months 31 days.
In order to ensure the accuracy of the calculation result of the solar voltage disturbance moment, the momentum wheel angular momentum data needs to be sampled for each fitting period. To reduce computational effort, consecutive samples may be taken for a sampling period or periods within the fitting period at the time of sampling, without taking samples for the entire fitting period.
The sampling mode of the momentum wheel angular momentum data can comprise two modes: firstly, acquiring on-orbit measured data of angular momentum of a momentum wheel under the condition that no additional interference moment such as ignition work of an electric thruster exists; and the second is estimated data calculated by using a ground calculation model simulating an on-orbit equivalent state.
Because each momentum wheel angular momentum data corresponds to time and position, and the solar light pressure interference moment can be calculated by using the momentum wheel angular momentum data, therefore, for each fitting period, the momentum wheel angular momentum data obtained by sampling in the fitting period can be converted into an equivalent measurement value of the solar light pressure interference moment, and then fitting is carried out according to the expression formula, so as to obtain fitting coefficients respectively corresponding to each fitting period
，/>
，/>
。
It should be noted that, the starting time of the fitting in the fitting process is the starting time of the solar light pressure period, for example, the solar light pressure period is 1 month, 1 day, 3 months and 31 days, and then the starting time may be 1 month, 1 day and 0 point.
It should be noted that, the steps 100-102 may be that the fitting coefficient of each period is stored in the satellite after the ground execution is completed, or the satellite may be obtained by on-orbit fitting based on the momentum wheel angular momentum data.
Then, for step 104, based on the fitting start time and the fitting start position of the satellite corresponding to different fitting periods in the solar photovoltaic cycle, the fitting time corresponding to the satellite at the forecast position is determined.
Since the correlation between the fitting time and the orbit position depends on the satellite position, when the satellite position changes, a new fitting time needs to be converted according to the time angle of the new position relative to the original position.
In one embodiment of the invention, the fitting time corresponding to the satellite at the forecast position can be calculated by 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 forecast position of the satellite;
for example, tsrp0=473155281s, sklon0=115°, sklon=125°, the cumulative seconds tsrp of the fitting time of the solar interference torque after the position change with respect to the satellite time reference is considered to be:
next, for step 106, a julian annual 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 annual difference and each fitting time period divided in the solar photovoltaic cycle.
In the embodiment of the invention, the forecast time can be the current time or a future time.
Specifically, the calculation method of the julian annual difference between the forecast time and the fitting time may include the following steps S1-S2:
s1, calculating a forecast moment and the fitting moment respectively relative to the julian years of the julian day standard;
in the embodiment of the invention, when the Greenner time of 2000 is 1 month 1 day 12 hours 0 minutes 0 seconds as the julian day reference, 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 )
wherein d_ jul _ta is julian day of the forecast time relative to the julian day reference, ta is the accumulated seconds of the forecast time relative to the star time reference, d_ jul0 is the julian day of the star time reference relative to the julian day reference, floor (x) is an integer taken downwards for x, J1, N1 and L1 are intermediate parameters, and Y_ jul _ta is the julian year of the forecast time relative to the julian day reference;
further, the julian years of the fitting moment relative to the julian day reference 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 julian day of the fitting time relative to the julian day reference, J2, N2 and L2 are intermediate parameters, and Y_ jul _srp is julian year of the fitting time relative to the julian day reference.
S2, taking the calculated difference value of the two julian years as the julian year difference between the forecasting 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 may be taken as the julian year difference.
For example, assuming that the star time reference is 0 minutes and 0 seconds on 1 month 1 day 0 of 2006, then the star time reference is d_ jul 0= 2191.5 relative to the julian day reference, thus obtaining tsrp= 473157681s, then the julian days d_ jul _srp and the julian years y_ jul _srp of tsrp relative to the julian day reference are:
d_jul_srp =7667.862
J2 =2459213
N2 =69
L2=7608
Y_jul_srp =20.8333
let the cumulative seconds of the forecasted time relative to the star time reference ta= 482661681s, then the julian day d_ jul _ta and julian year y_ jul _ta of the forecasted 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, it is necessary to determine the target fitting period matched with the forecast moment, specifically, the jth fitting period may be determined as the target fitting period by using the following formula:
wherein ceil (x) is an integer taken upward for x, numSRPdata is the total number of periods obtained after dividing the solar light pressure period into fitting periods; y_ jul _ta is the julian year of the forecast time relative to the julian day reference, and Y_ jul _srp is the julian year of the fitting time 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 can be calculated, and then the fitting coefficient corresponding to the 2 nd fitting period can be selected.
Finally, aiming at step 108, calculating the solar voltage disturbance moment at the forecasting time by using the fitting coefficient of the solar voltage disturbance moment of the target fitting period.
When the fitting coefficient of the j-th fitting period is selected, the solar voltage interference moment at the forecasting time at the forecasting position can be calculated based on the Fourier series expression
：
wherein ,
fitting coefficients for the j-th fitting period.
According to the embodiment of the invention, the fitting coefficient is obtained through the driving of the momentum wheel angular momentum data, and the solar light pressure interference moment on-orbit fitting calculation is adapted to the light pressure evolution rules of different positions and different time periods according to the conversion fitting time of different positions of the satellite. The method can be used for in-orbit calculation of solar pressure disturbance moment and in-orbit calculation of solar pressure shooting power, and is widely applicable to satellites with precise orbit determination or high-precision disturbance moment estimation requirements in stationary orbits.
As shown in fig. 2 and 3, the embodiment of the invention provides an on-orbit fitting estimation device for solar voltage interference moment of a stationary orbit satellite. The apparatus embodiments may be implemented by software, or may be implemented by hardware or a combination of hardware and software. In terms of hardware, as shown in fig. 2, a hardware architecture diagram of an electronic device where an on-orbit fitting device for solar voltage interference moment of a stationary orbit satellite provided by an embodiment of the present invention is located, besides a processor, a memory, a network interface, and a nonvolatile memory shown in fig. 2, the electronic device where the device is located in the embodiment may generally include other hardware, such as a forwarding chip responsible for processing a message, and so on. Taking a software implementation as an example, as shown in fig. 3, the device in a logic sense is formed by reading a corresponding computer program in a nonvolatile memory into a memory by a CPU of an electronic device where the device is located and running the computer program. The on-orbit fitting estimation device for the solar voltage interference moment of the stationary orbit satellite provided by the embodiment comprises:
the fitting coefficient obtaining unit 301 is configured to generate an expression formula of solar light pressure interference moment by using a fourier series form; the expression formula comprises a plurality of fitting coefficients; the solar photovoltaic cycle is divided into a plurality of fitting periods, each fitting period being performed: based on the momentum wheel angular momentum data obtained by sampling in the fitting period, taking the starting time of the solar light pressure period as the fitting starting time, converting the momentum wheel angular momentum data into an equivalent measurement value of the solar light pressure interference moment, and fitting according to the expression formula to obtain a fitting coefficient of the fitting period;
a first determining unit 302, configured to determine a fitting time corresponding to a predicted position of the satellite based on fitting start times corresponding to different fitting periods in the solar photovoltaic cycle and fitting start positions of the satellite;
a first calculating unit 303, configured to calculate a julian annual difference between a forecast time and the fitting time;
a second determining unit 304, configured to determine a target fitting period matched with the forecast time according to the julian annual difference and each fitting period divided in the solar photovoltaic cycle;
a second calculating unit 305, configured to calculate the solar voltage disturbance moment at the forecast time by using the fitting coefficient of the solar voltage disturbance moment of the target fitting period.
In one embodiment of the present invention, the expression formula is:
wherein ,T d as the interference moment of the sunlight pressure,Nin order to be a fourier series of orders,Tin the case of a solar light pressure cycle,Tas in the case of the track period,tin order to be time relative to the moment of start of the fitting,
，/>
，/>
is the fitting coefficient.
In one embodiment of the present invention, the first determining unit is specifically configured to calculate a fitting time corresponding to the satellite at the forecast location by using the following formula:
where tsrp is the cumulative seconds of the fitting time relative to the satellite time reference, tsrp0 is the cumulative seconds of the fitting start time relative to the satellite time reference, SKLon0 is the fitting start position of the satellite, and SKLon is the predicted position of the satellite.
In one embodiment of the present invention, the first calculating unit is specifically configured to calculate a julian year of the forecast time and the fitting time relative to a julian day reference, respectively; and taking the calculated difference value of the two julian years as the julian year difference between the forecast moment and the fitting moment.
In one embodiment of the present invention, the second determining unit is specifically configured to determine the j-th fitting period as the target fitting period by using the following formula:
wherein ceil (x) is an integer taken upward for x, numSRPdata is the total number of fitting periods obtained after dividing the solar photovoltaic period into fitting periods; y_ jul _ta is the julian year of the forecast time relative to the julian day reference, and Y_ jul _srp is the julian year of the fitting time relative to the julian day reference.
It will be appreciated that the structure illustrated in the embodiments of the present invention does not constitute a specific limitation on an on-orbit fitting device for the solar voltage disturbance moment of a stationary orbiting satellite. In other embodiments of the invention, an in-orbit fitting device for static orbital satellite solar pressure disturbance moment may include more or fewer components than shown, or may combine certain components, or split certain components, or a different arrangement of components. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.
The content of information interaction and execution process between the modules in the device is based on the same conception as the embodiment of the method of the present invention, and specific content can be referred to the description in the embodiment of the method of the present invention, which is not repeated here.
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 realizes the on-orbit fitting estimation method of the solar voltage interference moment of the stationary orbit satellite in any embodiment of the invention when executing the computer program.
The embodiment of the invention also provides a computer readable storage medium, and the computer readable storage medium is stored with a computer program, and the computer program when being executed by a processor, causes the processor to execute the on-orbit fitting estimation method of the static orbit satellite solar voltage interference moment in any embodiment of the invention.
Specifically, a system or apparatus provided with a storage medium on which a software program code realizing the functions of any of the above embodiments is stored, and a computer (or CPU or MPU) of the system or apparatus may be caused to read out and execute the program code stored in the storage medium.
In this case, the program code itself read from the storage medium may realize the functions of any of the above-described embodiments, and thus the program code and the storage medium storing the program code form part of the present invention.
Examples of the storage medium for providing 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 by a communication network.
Further, it should be apparent that the functions of any 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 part or all of the actual operations based on the instructions of the program code.
Further, it is understood that the program code read out by the storage medium is written into a memory provided in an expansion board inserted into a computer or into 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 and all of actual operations based on instructions of the program code, thereby realizing the functions of any of the above embodiments.
It is 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 additional identical elements in a process, method, article or apparatus that comprises the element.
Those of ordinary skill in the art will appreciate that: all or part of the steps for implementing the above method embodiments may be implemented by hardware related to program instructions, and the foregoing program may be stored in a computer readable storage medium, where the program, when executed, performs steps including the above method embodiments; and the aforementioned storage medium includes: various media in which program code may be stored, such as ROM, RAM, magnetic or optical disks.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the 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 scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. An on-orbit fitting estimation method for solar voltage disturbance moment of a stationary orbit satellite is characterized by comprising the following steps of:
generating an expression formula of solar light pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients;
the solar photovoltaic cycle is divided into a plurality of fitting periods, each fitting period being performed: based on the momentum wheel angular momentum data obtained by sampling in the fitting period, taking the starting time of the solar light pressure period as the fitting starting time, converting the momentum wheel angular momentum data into an equivalent measurement value of the solar light pressure interference moment, and fitting according to the expression formula to obtain a fitting coefficient of the fitting period;
determining fitting time corresponding to a predicted position of a satellite based on fitting starting time corresponding to different fitting time periods in a solar photovoltaic period and fitting starting positions of the satellite;
calculating the julian annual difference between the forecasting time and the fitting time, and determining a target fitting time period matched with the forecasting time according to the julian annual difference and each fitting time period divided in the solar light pressure period;
calculating the solar voltage disturbance moment at the forecast moment by using the fitting coefficient of the solar voltage disturbance moment at the target fitting period;
the expression formula is as follows:
wherein ,T d as the interference moment of the sunlight pressure,Nin order to be a fourier series of orders,Tin the case of a solar light pressure cycle,Tas in the case of the track period,tin order to be time relative to the moment of start of the fitting,A 0 ，A i ，B i fitting coefficients;
the 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 solar photovoltaic period and the fitting starting position of the satellite comprises the following steps:
calculating fitting time corresponding to 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 forecast position of the satellite;
the determining a target fitting period matched with the forecasting time according to the julian annual difference and each fitting period divided in the solar photovoltaic cycle comprises the following steps:
the j-th fitting period is determined as the target fitting period using the following formula:
wherein ceil (x) is an integer taken up for x, floor (x) is an integer taken down for x, numSRPdata is the total number of fitting periods obtained after dividing the solar photovoltaic period into fitting periods; y_ jul _ta is the julian year of the forecast time relative to the julian day reference, and Y_ jul _srp is the julian year of the fitting time relative to the julian day reference.
2. The method of claim 1, wherein calculating the julian annual difference between the forecasted time and the fitted time comprises:
calculating the pre-measurement time and the fitting time respectively relative to the julian day reference;
and taking the calculated difference value of the two julian years as the julian year difference between the forecast moment and the fitting moment.
3. An on-orbit fitting estimation device for solar voltage disturbance moment of a stationary orbit satellite, which is characterized by comprising:
the fitting coefficient acquisition unit is used for generating an expression formula of solar light pressure interference moment by utilizing a Fourier series form; the expression formula comprises a plurality of fitting coefficients; the solar photovoltaic cycle is divided into a plurality of fitting periods, each fitting period being performed: based on the momentum wheel angular momentum data obtained by sampling in the fitting period, taking the starting time of the solar light pressure period as the fitting starting time, converting the momentum wheel angular momentum data into an equivalent measurement value of the solar light pressure interference moment, and fitting according to the expression formula to obtain a fitting coefficient of the fitting period;
the first determining unit is used for determining fitting time corresponding to the satellite at the forecast position based on fitting starting time corresponding to different fitting time periods in the solar photovoltaic period and the fitting starting position of the satellite;
the first calculation unit is used for calculating the julian annual difference between the forecast time and the fitting time;
the second determining unit is used for determining a target fitting period matched with the forecasting time according to the slightly annual difference and each fitting period divided in the solar light pressure period;
the second calculation unit is used for calculating the solar voltage disturbance moment at the forecasting time by utilizing the fitting coefficient of the solar voltage disturbance moment of the target fitting period;
the expression formula is as follows:
wherein ,T d as the interference moment of the sunlight pressure,Nin order to be a fourier series of orders,Tin the case of a solar light pressure cycle,Tas in the case of the track period,tin order to be time relative to the moment of start of the fitting,A 0 ，A i ，B i fitting coefficients;
the first determining unit is specifically configured to:
calculating fitting time corresponding to 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 forecast position of the satellite;
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 integer taken up for x, floor (x) is an integer taken down for x, numSRPdata is the total number of fitting periods obtained after dividing the solar photovoltaic period into fitting periods; y_ jul _ta is the julian year of the forecast time relative to the julian day reference, and Y_ jul _srp is the julian year of the fitting time relative to the julian day reference.
4. The apparatus of claim 3, wherein the device comprises a plurality of sensors,
the first calculation unit is specifically configured to calculate a julian year of the forecast time and the fitting time relative to a julian day reference respectively; and taking the calculated difference value of the two julian years as the julian year difference between the forecast moment and the fitting moment.
5. An electronic device comprising a memory and a processor, the memory having stored therein a computer program, the processor implementing the method of any of claims 1-2 when the computer program is executed.
6. A computer readable storage medium having stored thereon a computer program which, when executed in a computer, causes the computer to perform the method of any of claims 1-2.
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