CN116147573A - Satellite orbit drift monitoring method, device and equipment - Google Patents
Satellite orbit drift monitoring method, device and equipment Download PDFInfo
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Abstract
The invention discloses a satellite orbit drift monitoring method, device and equipment, relates to the technical field of satellite monitoring, and is used for solving the problems of high algorithm difficulty, complex working mode and low precision used in the satellite orbit drift monitoring method in the prior art. Comprising the following steps: selecting orbit information of a satellite orbit with a solar synchronous freezing regression orbit characteristic in two adjacent cycle periods; determining first longitude and latitude information and second longitude and latitude information corresponding to points of the cycle period, which are nearest to equator, in the southern hemisphere and the northern hemisphere; interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined; the drift distance of the satellite orbit is determined based on the first longitude value and the second longitude value corresponding to the previous cycle period, so that the drift monitoring of the satellite orbit is realized.
Description
Technical Field
The present invention relates to the field of satellite monitoring technologies, and in particular, to a method, an apparatus, and a device for monitoring satellite orbit drift.
Background
With the rapid development of satellite technologies, the types and the number of satellites are increasing, and in order to ensure the normal operation of the satellites, the states of the satellites need to be monitored, for example: monitoring of satellite orbits. The satellite orbit is susceptible to various spatial factors, and its orbit gradually deviates from the earth's equatorial plane with time, and the orbit inclination gradually increases from 0 °, for example: the orbits of satellites in orbit change during their orbit due to the influence of the attraction of the satellites. Therefore, in order to ensure that the satellite runs on a predetermined orbit, monitoring and early warning are required in time when the satellite orbit changes.
At present, satellite orbit state monitoring methods are realized by manually recording satellite orbit operation data to calculate satellite orbit drift conditions or by a ground measurement and control center based on pseudo-range telemetry signal tracking, and the methods have the advantages of high algorithm difficulty, complex working mode and low precision.
Accordingly, there is a need to provide a more reliable satellite orbit drift monitoring scheme.
Disclosure of Invention
The invention aims to provide a satellite orbit drift monitoring method, device and equipment, which are used for solving the problems of high algorithm difficulty, complex working mode and low precision used in the satellite orbit drift monitoring method in the prior art.
In order to achieve the above object, the present invention provides the following technical solutions:
in a first aspect, the present invention provides a satellite orbit drift monitoring method, the method comprising:
selecting orbit information of two adjacent cycle periods of a satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
for any cycle, determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the southern hemisphere, and determining second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere;
interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined;
and determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
Compared with the prior art, the satellite orbit drift monitoring method provided by the invention has the advantages that the orbit information of the satellite orbit with the characteristic of solar synchronous freezing regression orbit in two adjacent cycle periods is selected; for any cycle, determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the southern hemisphere, and determining second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere; interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined; the method is simple in calculation, can rapidly monitor the drifting condition of the satellite orbit, and is high in monitoring precision.
In a second aspect, the present invention provides a satellite orbit drift monitoring device, which includes:
the orbit information selecting module is used for selecting the orbit information of two adjacent cycle periods of the satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
the target longitude and latitude information determining module is used for determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere and second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere for any cycle;
the interpolation processing module is used for carrying out interpolation processing based on the first longitude and latitude information and the second longitude and latitude information and determining a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period;
and the satellite orbit drift monitoring module is used for determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
In a third aspect, the present invention provides a satellite orbit drift monitoring device, the device comprising:
the communication unit/communication interface is used for selecting the orbit information of two adjacent cycle periods of the satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
the processing unit/processor is used for determining first longitude and latitude information corresponding to a point, closest to the equator, of the northern hemisphere in the current cycle period and determining second longitude and latitude information corresponding to a point, closest to the equator, of the northern hemisphere in the current cycle period;
interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined;
and determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
In a fourth aspect, the present invention provides a computer storage medium having instructions stored therein that, when executed, implement the satellite orbit drift monitoring method described above.
Technical effects achieved by the apparatus class scheme provided in the second aspect, the device class scheme provided in the third aspect, and the computer storage medium scheme provided in the fourth aspect are the same as those achieved by the method class scheme provided in the first aspect, and are not described herein.
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The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:
FIG. 1 is a schematic flow chart of a satellite orbit drift monitoring method provided by the invention;
FIG. 2 is a schematic diagram of the overall implementation process of the satellite orbit drift monitoring method provided by the invention;
FIG. 3 is a schematic diagram of a satellite orbit drift monitoring device according to the present invention;
fig. 4 is a schematic structural diagram of a satellite orbit drift monitoring device provided by the invention.
Detailed Description
In order to clearly describe the technical solution of the embodiments of the present invention, in the embodiments of the present invention, the words "first", "second", etc. are used to distinguish the same item or similar items having substantially the same function and effect. For example, the first threshold and the second threshold are merely for distinguishing between different thresholds, and are not limited in order. It will be appreciated by those of skill in the art that the words "first," "second," and the like do not limit the amount and order of execution, and that the words "first," "second," and the like do not necessarily differ.
In the present invention, the words "exemplary" or "such as" are used to mean serving as an example, instance, or illustration. Any embodiment or design described herein as "exemplary" or "for example" should not be construed as preferred or advantageous over other embodiments or designs. Rather, the use of words such as "exemplary" or "such as" is intended to present related concepts in a concrete fashion.
In the present invention, "at least one" means one or more, and "a plurality" means two or more. "and/or", describes an association relationship of an association object, and indicates that there may be three relationships, for example, a and/or B, and may indicate: a alone, a and B together, and B alone, wherein a, B may be singular or plural. The character "/" generally indicates that the context-dependent object is an "or" relationship. "at least one of" or the like means any combination of these items, including any combination of single item(s) or plural items(s). For example, at least one (one) of a, b or c may represent: a, b, c, a and b, a and c, b and c, or a, b and c, wherein a, b, c can be single or multiple.
In order to ensure that the satellite runs on a predetermined orbit, monitoring and early warning are required to be performed in time when the orbit of the satellite changes. At present, the state monitoring method of the satellite orbit is realized by a ground measurement and control center based on pseudo-range telemetry signal tracking, the monitoring algorithm adopted in the prior art is multiple in variety, high in algorithm difficulty, low in data selection accuracy, more in dependence on external factors, complex in working mode and low in accuracy.
Accordingly, the present invention provides a fast and simple satellite orbit drift monitoring scheme, and the scheme provided in the embodiments of the present specification will be described below with reference to the accompanying drawings:
as shown in fig. 1, the process may include the steps of:
step 110: selecting orbit information of two adjacent cycle periods of a satellite orbit; the satellite orbit is an orbit having a characteristic of a freeze-back orbit of solar synchronization.
The satellite can fly around the earth without any power after only obtaining the speed in the horizontal direction, and the flying track of the satellite is called a satellite orbit. The satellite orbit in the invention is an orbit with the characteristic of freezing return orbit of solar synchronization, the direction of the arch line of the frozen orbit is fixed, the eccentricity is small, the altitude of the space above latitude areas such as the satellite fly over is the same, the satellite orbit is very beneficial to scientific measurement of vertical section of geodetic survey and the like, and is often used for atmospheric detection satellites, ocean satellites, terrestrial satellites and the like. Freezing the return orbit characteristics may require that the precession of the orbit surface be synchronized with the annual apparent motion of the flat sun, i.e., sun-synchronized orbit, so that the satellite has similar lighting conditions when observing the same latitudes area, and that the satellite passes over the same area again after a certain period is separated, i.e., return orbit, to dynamically monitor the satellite, and further that the satellite is at the same altitude and speed as possible when passing through the same area.
When selecting the orbit information, the satellite orbit information can be extracted according to the input satellite data file name, for example: defined as Cycle and Pass, wherein Pass number is a single fixed value; and retrieving the data track information of the adjacent previous Cycle according to the Cycle and Pass numbers, wherein the data track information is Cycle-1 and Pass.
Step 120: for any one cycle period, determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle period in the southern hemisphere, and determining second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle period in the northern hemisphere.
Screening the data closest to the equator in the two adjacent periods selected in the step 110 for the two points closest to the equator in the data track of the current cycle period in the north-south hemisphere
and />
And determining longitude and latitude information corresponding to two points closest to the equator in each cycle period.
Step 130: and carrying out interpolation processing based on the first longitude and latitude information and the second longitude and latitude information, and determining a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period.
Interpolation processing may refer to processing using interpolation algorithms, which may exist in a variety of ways, such as: bilinear interpolation, nearest zero interpolation, etc. In the invention, the latitude of the point of each cycle, which is closest to the equator, in the north and south hemispheres is screened, after longitude information corresponding to the latitude information of the point, which is closest to the equator, in the south hemispheres is obtained according to the screened latitude information of the point, which is closest to the equator, in the north hemispheres, interpolation processing is carried out on the latitude values of the north hemispheres and the south hemispheres in the two cycle tracks, the proportion value used for linear interpolation when the equator is crossed is recorded, the proportion value is utilized to carry out equal proportion linear interpolation on the longitude information corresponding to the two points, which are closest to the equator, in the south hemispheres and the north hemispheres, and the longitude value corresponding to the track when the track passes through the equator is recorded.
Step 140: and determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
Obtaining the distance (in meters) of satellite orbit drift by calculating the position difference when two adjacent cycle orbits pass through the equator by using the longitude information of the over-equator; and judging whether the satellite orbit drifts or not according to a preset orbit drift threshold value.
The method in fig. 1 is implemented by selecting orbit information of a satellite orbit with a solar synchronous frozen return orbit characteristic in two adjacent cycle periods; for any cycle, determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the southern hemisphere, and determining second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere; interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined; the method is simple in calculation, can rapidly monitor the drifting condition of the satellite orbit, and is high in monitoring precision.
Based on the method of fig. 1, the examples of the present specification also provide some specific implementations of the method, as described below.
The first longitude and latitude information may include first latitude information and first longitude information; the second latitude and longitude information may include second latitude information and second longitude information;
interpolation processing is performed based on the first longitude and latitude information and the second longitude and latitude information, and determining a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period specifically may include:
performing interpolation processing on the first latitude information and the second latitude information, and recording a proportion value used by linear interpolation when the track passes through the equator;
and performing equal-proportion linear interpolation on the first longitude information and the second longitude information by using the proportion value, and recording a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period.
For the previous cycle, interpolation processing is carried out on latitude information corresponding to the point, closest to the equator, of the north-south hemisphere in the previous cycle, and a second longitude value corresponding to the moment that the satellite orbit passes through the equator in the previous cycle is determined;
determining a corresponding position difference when two adjacent cycle orbits pass through the equator by utilizing the first longitude value and the second longitude value;
determining a drift distance of the satellite orbit based on the position difference;
comparing the drift distance with a preset track drift threshold value to obtain a comparison result;
and judging whether the satellite orbit drifts or not based on the comparison result.
Calculating the difference between the first longitude value and the second longitude value to obtain a corresponding longitude difference when two adjacent cycle orbits pass through the equator;
converting the longitude difference into a position difference;
judging whether the satellite orbit drifts or not based on the comparison result, specifically comprising:
and if the drift distance exceeds a preset orbit drift threshold value, determining that the satellite orbit drift is abnormal.
As shown in fig. 2, the overall implementation steps of the scheme are as follows:
screening the data closest to the equator in the two adjacent periods selected in the step 110 for the two points closest to the equator in the data track of the current cycle period in the north-south hemisphere
and />
Afterwards, recording the corresponding position information (Lon1_north, lat1_north) and (Lon1_south, lat1_south); screening the data track of the previous cycle for two points nearest to the equator in the southern and northern hemispheres +.>
and />
And recording the corresponding position information (Lon2_north, lat2_north) and (Lon2_south, lat2_south);
performing linear interpolation on two points, which are closest to the equator, of the north and south hemispheres, and recording position information when the track passes through the equator, performing linear interpolation on two points, which are closest to the equator, of the north and south hemispheres of the current cycle, recording position information [ Lon1, 0 DEG ] when the track passes through the equator, and recording a linear interpolation relation Line1; and (3) performing linear interpolation on two points, which are positioned on the south hemisphere and the north hemisphere and are closest to the equator, of the orbit in the previous cycle period, recording the position information [ Lon2, 0 DEG ] of the orbit when the orbit passes through the equator, and recording a linear interpolation relation Line2.
Calculating a longitude difference between the acquired Lon1 and Lon2 according to the acquired Lon1 and Lon2, and converting the longitude difference into a distance Dis (Km); and comparing Dis with a track drift monitoring threshold value, and judging that the track drift is abnormal when the threshold value is exceeded. In practice, the track drift threshold is generally smaller, so that the aim of early warning can be fulfilled.
The determining the first longitude and latitude information corresponding to the point of the current cycle closest to the equator in the southern hemisphere and the second longitude and latitude information corresponding to the point of the current cycle closest to the equator in the northern hemisphere may specifically include:
determining the maximum latitude value of all latitude information corresponding to the southern hemisphere in the current cycle period, determining the maximum latitude value as first latitude information corresponding to the point of the current cycle period nearest to the equator in the southern hemisphere, and acquiring first longitude information corresponding to the first latitude information;
and determining the minimum latitude value of all latitude information corresponding to the northern hemisphere in the current cycle period, determining the minimum latitude value as second latitude information corresponding to the point of the northern hemisphere closest to the equator in the current cycle period, and acquiring second longitude information corresponding to the second latitude information.
In screening the latitudes of the north and south points closest to the equator, the following expression may be used:
recording position index information N1_solution, N2_solution and N2_solution corresponding to Lat1_solution, lat2_solution and Lat2_solution; and longitude information Lon 1-solution, lon 2-solution and Lon 2-solution corresponding to Lat 1-solution, lat 2-solution and Lat 2-solution is obtained according to the position index information.
Optionally, determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, and after implementing the drift monitoring of the satellite orbit, further includes:
long time series information is introduced to make an overall assessment of the overall orbital drift conditions of the satellite during its orbit.
The time series is a series formed by arranging the numerical values of a certain statistical index of a certain phenomenon at different times in time sequence. The long time series information may include information corresponding to satellites during orbit.
After the orbital drift of the satellite is monitored using the method of fig. 1, the overall assessment of the satellite's orbit conditions during orbit can be made by introducing long time series information.
In the above technical solution, the interpolation processing is performed on the first latitude information and the second latitude information, and the proportion value used in the linear interpolation when the track passes through the equator is recorded, where the proportion value may also be referred to as a linear interpolation relationship, and the linear interpolation interpolates the current period lat1_north and lat1_south and interpolates the Lon1_north and Lon1_south by using the same linear interpolation relationship Line1; interpolation of lat2_north and lat2_south of the previous cycle period, and interpolation of Lon2_north and Lon2_south are performed using the same linear interpolation relationship Line2, and the corresponding linear interpolation relationship Line1 may be expressed as formula (1):
wherein in formula (1)
Representing a scale value used for linear interpolation when the track passes through the equator; />
Represents the nearest point from the equator in the southern hemisphere, < >>
Representing the closest point to the equator in the northern hemisphere; />
Representation->
The distance of the point from the equator; />
Representation->
Point to->
Distance of the points.
Interpolation is carried out on the current period Lat1_north and Lat1_south by using the same linear interpolation relation Line1, and interpolation is carried out on the Lon1_north and Lon1_south; and interpolating Lat2_north and Lat2_south of the previous cycle period and Lon2_north and Lon2_south by using the same linear interpolation relation Line2.
The corresponding linear interpolation relationship Line2 can be expressed as formula (2):
wherein in formula (2)
Is->
Distance to the equator; />
Is->
To->
Is a distance of (3). The acquired Lon1 and Lon2 calculate the longitude difference between the two, and convert the longitude difference into a distance Dis (in Km); and comparing Dis with a track drift monitoring threshold, judging that the track drift is abnormal when the Dis exceeds the threshold, and judging that the track drift is normal when the Dis does not exceed the threshold. In practice, the track drift threshold is generally smaller, so that the aim of early warning can be fulfilled.
The technical scheme provided by the invention directly utilizes the satellite data of two adjacent cycle periods to calculate the orbital drift condition of the in-orbit satellite. The method is simple in calculation, and the orbital drift condition of the in-orbit satellite can be calculated rapidly. By introducing time sequence information, the orbital drift condition of the long-time sequence of the on-orbit satellite can be monitored and early-warned.
Based on the same thought, the invention also provides an engine centrifugal pump simulation device, as shown in fig. 3, the device can comprise:
the orbit information selection module 310 is configured to select orbit information of two adjacent cycle periods of the satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
the target longitude and latitude information determining module 320 is configured to determine, for any cycle period, first longitude and latitude information corresponding to a point of the current cycle period closest to the equator in the southern hemisphere, and second longitude and latitude information corresponding to a point of the current cycle period closest to the equator in the northern hemisphere;
the interpolation processing module 330 is configured to perform interpolation processing based on the first longitude and latitude information and the second longitude and latitude information, and determine a first longitude value corresponding to a current cycle period when the satellite orbit passes through the equator;
the satellite orbit drift monitoring module 340 is configured to determine a drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in a previous cycle period, so as to realize drift monitoring of the satellite orbit.
Based on the apparatus in fig. 3, some specific implementation units may also be included:
optionally, the first latitude information may include first latitude information and first longitude information; the second latitude and longitude information may include second latitude information and second longitude information;
the interpolation processing module 330 may specifically include:
the first interpolation processing unit is used for carrying out interpolation processing on the first latitude information and the second latitude information and recording a proportion value used by linear interpolation when the track passes through the equator;
and the second interpolation processing unit is used for performing equal-proportion linear interpolation on the first longitude information and the second longitude information by utilizing the proportion value, and recording a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period.
Optionally, the satellite orbit drift monitoring module 340 may specifically include:
the second longitude value determining unit is used for carrying out interpolation processing on latitude information corresponding to a point, closest to the equator, of the north-south hemisphere in the previous cycle period, and determining a second longitude value corresponding to the moment that the satellite orbit passes through the equator in the previous cycle period;
a position difference determining unit configured to determine a position difference corresponding to when two adjacent cyclic orbits pass through the equator using the first longitude value and the second longitude value;
a drift distance determining unit configured to determine a drift distance of the satellite orbit based on the position difference;
the comparison unit is used for comparing the drift distance with a preset track drift threshold value to obtain a comparison result;
and the drift judging unit is used for judging whether the satellite orbit drifts or not based on the comparison result.
Optionally, the position difference determining unit may specifically be configured to:
calculating the difference between the first longitude value and the second longitude value to obtain a corresponding longitude difference when two adjacent cycle orbits pass through the equator;
converting the longitude difference into a position difference;
the drift judgment unit may specifically be configured to:
and if the drift distance exceeds a preset orbit drift threshold value, determining that the satellite orbit drift is abnormal.
Optionally, the target longitude and latitude information determining module 320 may be specifically configured to:
determining the maximum latitude value of all latitude information corresponding to the southern hemisphere in the current cycle period, determining the maximum latitude value as first latitude information corresponding to the point of the current cycle period nearest to the equator in the southern hemisphere, and acquiring first longitude information corresponding to the first latitude information;
and determining the minimum latitude value of all latitude information corresponding to the northern hemisphere in the current cycle period, determining the minimum latitude value as second latitude information corresponding to the point of the northern hemisphere closest to the equator in the current cycle period, and acquiring second longitude information corresponding to the second latitude information.
Optionally, the apparatus may further include:
and the drift condition overall evaluation module is used for introducing long-time sequence information and performing overall evaluation on the overall orbit drift condition of the satellite during the orbit.
Alternatively, the ratio value may be expressed as the formula:
wherein ,
representing a scale value used for linear interpolation when the track passes through the equator; />
Represents the nearest point from the equator in the southern hemisphere, said +.>
Representing the closest point to the equator in the northern hemisphere; />
Representation->
The distance of the point from the equator; />
Representation->
Point to->
Distance of the points.
Based on the same thought, the embodiment of the specification also provides satellite orbit drift monitoring equipment. As shown in fig. 4, may include:
the communication unit/communication interface is used for selecting the orbit information of two adjacent cycle periods of the satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
the processing unit/processor is used for determining first longitude and latitude information corresponding to a point, closest to the equator, of the northern hemisphere in the current cycle period and determining second longitude and latitude information corresponding to a point, closest to the equator, of the northern hemisphere in the current cycle period;
interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined;
and determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
As shown in fig. 4, the terminal device may further include a communication line. The communication line may include a pathway to communicate information between the aforementioned components.
Optionally, as shown in fig. 4, the terminal device may further include a memory. The memory is used for storing computer-executable instructions for executing the scheme of the invention, and the processor is used for controlling the execution. The processor is configured to execute computer-executable instructions stored in the memory, thereby implementing the method provided by the embodiment of the invention.
In a specific implementation, as one embodiment, as shown in FIG. 4, the processor may include one or more CPUs, such as CPU0 and CPU1 in FIG. 4.
In a specific implementation, as an embodiment, as shown in fig. 4, the terminal device may include a plurality of processors, such as the processors in fig. 4. Each of these processors may be a single-core processor or a multi-core processor.
Based on the same thought, the embodiments of the present disclosure further provide a computer storage medium corresponding to the above embodiments, where instructions are stored, and when the instructions are executed, the method in the above embodiments is implemented.
The above description has been presented mainly in terms of interaction between the modules, and the solution provided by the embodiment of the present invention is described. It is understood that each module, in order to implement the above-mentioned functions, includes a corresponding hardware structure and/or software unit for performing each function. Those of skill in the art will readily appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as hardware or combinations of hardware and computer software. Whether a function is implemented as hardware or computer software driven hardware depends upon the particular application and design constraints imposed on the solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
The embodiment of the invention can divide the functional modules according to the method example, for example, each functional module can be divided corresponding to each function, or two or more functions can be integrated in one processing module. The integrated modules may be implemented in hardware or in software functional modules. It should be noted that, in the embodiment of the present invention, the division of the modules is schematic, which is merely a logic function division, and other division manners may be implemented in actual implementation.
The processor in this specification may also have a function of a memory. The memory is used for storing computer-executable instructions for executing the scheme of the invention, and the processor is used for controlling the execution. The processor is configured to execute computer-executable instructions stored in the memory, thereby implementing the method provided by the embodiment of the invention.
The memory may be, but is not limited to, read-only memory (ROM) or other type of static storage device that can store static information and instructions, random access memory (random access memory, RAM) or other type of dynamic storage device that can store information and instructions, but may also be electrically erasable programmable read-only memory (EEPROM), compact disc-read only memory (compact disc read-only memory) or other optical disk storage, optical disk storage (including compact disc, laser disc, optical disc, digital versatile disc, blu-ray disc, etc.), magnetic disk storage media or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer. The memory may be stand alone and be coupled to the processor via a communication line. The memory may also be integrated with the processor.
Alternatively, the computer-executable instructions in the embodiments of the present invention may be referred to as application program codes, which are not particularly limited in the embodiments of the present invention.
The method disclosed by the embodiment of the invention can be applied to a processor or realized by the processor. The processor may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or by instructions in the form of software. The processor may be a general purpose processor, a digital signal processor (digital signal processing, DSP), an ASIC, an off-the-shelf programmable gate array (field-programmable gate array, FPGA) or other programmable logic device, discrete gate or transistor logic device, discrete hardware components. The disclosed methods, steps, and logic blocks in the embodiments of the present invention may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present invention may be embodied directly in the execution of a hardware decoding processor, or in the execution of a combination of hardware and software modules in a decoding processor. The software modules may be located in a random access memory, flash memory, read only memory, programmable read only memory, or electrically erasable programmable memory, registers, etc. as well known in the art. The storage medium is located in a memory, and the processor reads the information in the memory and, in combination with its hardware, performs the steps of the above method.
In a possible implementation manner, a computer readable storage medium is provided, where instructions are stored, and when the instructions are executed, the computer readable storage medium is used to implement the method in the above embodiment.
In the above embodiments, it may be implemented in whole or in part by software, hardware, firmware, or any combination thereof. When implemented in software, may be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer programs or instructions. When the computer program or instructions are loaded and executed on a computer, the processes or functions described in the embodiments of the present invention are performed in whole or in part. The computer may be a general purpose computer, a special purpose computer, a computer network, a terminal, a user equipment, or other programmable apparatus. The computer program or instructions may be stored in a computer readable storage medium or transmitted from one computer readable storage medium to another computer readable storage medium, for example, the computer program or instructions may be transmitted from one website site, computer, server, or data center to another website site, computer, server, or data center by wired or wireless means. The computer readable storage medium may be any available medium that can be accessed by a computer or a data storage device such as a server, data center, etc. that integrates one or more available media. The usable medium may be a magnetic medium, e.g., floppy disk, hard disk, tape; optical media, such as digital video discs (digital video disc, DVD); but also semiconductor media such as solid state disks (solid state drive, SSD).
Although the invention is described herein in connection with various embodiments, other variations to the disclosed embodiments can be understood and effected by those skilled in the art in practicing the claimed invention, from a study of the drawings, the disclosure, and the appended claims. In the claims, the word "comprising" does not exclude other elements or steps, and the "a" or "an" does not exclude a plurality. A single processor or other unit may fulfill the functions of several items recited in the claims. The mere fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage.
Although the invention has been described in connection with specific features and embodiments thereof, it will be apparent that various modifications and combinations can be made without departing from the spirit and scope of the invention. Accordingly, the specification and drawings are merely exemplary illustrations of the present invention as defined in the appended claims and are considered to cover any and all modifications, variations, combinations, or equivalents that fall within the scope of the invention. It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (10)
1. A method for monitoring satellite orbit drift, the method comprising:
selecting orbit information of two adjacent cycle periods of a satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
for any cycle, determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the southern hemisphere, and determining second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere;
interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined;
and determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
2. The satellite orbit drift monitoring method of claim 1, wherein the first latitude and longitude information comprises first latitude and longitude information; the second longitude and latitude information comprises second latitude information and second longitude information;
interpolation processing is performed based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined, which specifically comprises the following steps:
performing interpolation processing on the first latitude information and the second latitude information, and recording a proportion value used by linear interpolation when the track passes through the equator;
and performing equal-proportion linear interpolation on the first longitude information and the second longitude information by using the proportion value, and recording a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period.
3. The method for monitoring the drift of a satellite orbit according to claim 2, wherein the drift distance of the satellite orbit is determined based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit, and specifically comprising:
for the previous cycle, interpolation processing is carried out on latitude information corresponding to the point, closest to the equator, of the north-south hemisphere in the previous cycle, and a second longitude value corresponding to the moment that the satellite orbit passes through the equator in the previous cycle is determined;
determining a corresponding position difference when two adjacent cycle orbits pass through the equator by utilizing the first longitude value and the second longitude value;
determining a drift distance of the satellite orbit based on the position difference;
comparing the drift distance with a preset track drift threshold value to obtain a comparison result;
and judging whether the satellite orbit drifts or not based on the comparison result.
4. A satellite orbit drift monitoring method according to claim 3, characterized in that determining the corresponding position difference when two adjacent cyclic orbits pass the equator by using the first longitude value and the second longitude value, comprises:
calculating the difference between the first longitude value and the second longitude value to obtain a corresponding longitude difference when two adjacent cycle orbits pass through the equator;
converting the longitude difference into a position difference;
judging whether the satellite orbit drifts or not based on the comparison result, specifically comprising:
and if the drift distance exceeds a preset orbit drift threshold value, determining that the satellite orbit drift is abnormal.
5. The method for monitoring satellite orbit drift according to claim 1, wherein determining the first latitude and longitude information corresponding to the point of the current cycle closest to the equator in the southern hemisphere and determining the second latitude and longitude information corresponding to the point of the current cycle closest to the equator in the northern hemisphere specifically comprises:
determining the maximum latitude value of all latitude information corresponding to the southern hemisphere in the current cycle period, determining the maximum latitude value as first latitude information corresponding to the point of the current cycle period nearest to the equator in the southern hemisphere, and acquiring first longitude information corresponding to the first latitude information;
and determining the minimum latitude value of all latitude information corresponding to the northern hemisphere in the current cycle period, determining the minimum latitude value as second latitude information corresponding to the point of the northern hemisphere closest to the equator in the current cycle period, and acquiring second longitude information corresponding to the second latitude information.
6. The method according to claim 1, wherein determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, after implementing the satellite orbit drift monitoring, further comprises:
long time series information is introduced to make an overall assessment of the overall orbital drift conditions of the satellite during its orbit.
7. The satellite orbit drift monitoring method according to claim 2, wherein the ratio value is expressed as the formula:
wherein ,
representing a scale value used for linear interpolation when the track passes through the equator; />
Represents the nearest point from the equator in the southern hemisphere, < >>
Representing the closest point to the equator in the northern hemisphere; />
Representation->
The distance of the point from the equator; />
Representation->
Point to->
Distance of the points.
8. A satellite orbit drift monitoring device, comprising:
the orbit information selecting module is used for selecting the orbit information of two adjacent cycle periods of the satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
the target longitude and latitude information determining module is used for determining first longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere and second longitude and latitude information corresponding to a point, closest to the equator, of the current cycle in the northern hemisphere for any cycle;
the interpolation processing module is used for carrying out interpolation processing based on the first longitude and latitude information and the second longitude and latitude information and determining a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period;
and the satellite orbit drift monitoring module is used for determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
9. A satellite orbit drift monitoring device, the device comprising:
the communication unit/communication interface is used for selecting the orbit information of two adjacent cycle periods of the satellite orbit; the satellite orbit is an orbit with the characteristic of a solar synchronous freezing regression orbit;
the processing unit/processor is used for determining first longitude and latitude information corresponding to a point, closest to the equator, of the northern hemisphere in the current cycle period and determining second longitude and latitude information corresponding to a point, closest to the equator, of the northern hemisphere in the current cycle period;
interpolation processing is carried out based on the first longitude and latitude information and the second longitude and latitude information, and a first longitude value corresponding to the moment that the satellite orbit passes through the equator in the current cycle period is determined;
and determining the drift distance of the satellite orbit based on the first longitude value and a second longitude value corresponding to the satellite orbit passing through the equator in the previous cycle period, so as to realize the drift monitoring of the satellite orbit.
10. A computer storage medium having instructions stored therein which, when executed, implement the satellite orbit drift monitoring method of any one of claims 1 to 7.
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