Satellite ephemeris updating method and device and satellite-borne equipment

Abstract

The embodiment of the invention provides a satellite ephemeris updating method and device and spaceborne equipment, and relates to the technical field of aerospace, and the method comprises the steps: obtaining the current position and current space environment parameters of a satellite; searching a grid adjacent to the current position from the plurality of grids, wherein the grid is associated with the position, the space environment parameter interval and the atmospheric density; predicting the atmospheric density of the orbit where the satellite is located by using the position, the space environment parameter interval and the atmospheric density associated with the adjacent grids, the current position and the current space environment parameters; and updating the ephemeris of the satellite by using the predicted atmospheric density. By applying the technical scheme provided by the embodiment of the invention, the prediction precision of the atmospheric density can be improved and the satellite ephemeris prediction precision can be improved under the condition that the computing power and storage of satellite-borne equipment are limited.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a satellite ephemeris updating method, device and satellite-borne equipment. Background Art

[0002] During satellite navigation, satellite ephemeris needs to be broadcasted in ultra-real time. In order to obtain ultra-real-time ephemeris, the atmospheric density of the satellite orbit needs to be accurately predicted. At present, due to the limited computing power and storage of onboard equipment, the onboard atmospheric density prediction scheme uses a low-precision exponential atmospheric density model to predict atmospheric density. This scheme cannot meet users' needs for high-precision prediction of atmospheric density and ephemeris. Summary of the invention

[0003] The purpose of the embodiments of the present application is to provide a satellite ephemeris update method, device and satellite-borne equipment, so as to improve the prediction accuracy of atmospheric density and improve the high-precision prediction of satellite ephemeris when the computing power and storage of the satellite-borne equipment are limited. The specific technical solution is as follows:

[0004] In a first aspect, an embodiment of the present application provides a method for updating satellite ephemeris, the method comprising:

[0005] Get the current position of the satellite and the current space environment parameters;

[0006] Searching for a neighboring grid of the current position from a plurality of grids, wherein the grid is associated with a position, a space environment parameter interval, and an atmospheric density;

[0007] Predicting the atmospheric density of the orbit where the satellite is located by using the position, space environment parameter interval and atmospheric density associated with the adjacent grids, as well as the current position and the current space environment parameter;

[0008] The predicted atmospheric density is used to update the satellite's ephemeris.

[0009] In some embodiments, the association between the grid and the position, the space environment parameter interval and the atmospheric density is determined according to the orbital altitude and mission period of the satellite.

[0010] In some embodiments, the location includes altitude, latitude, and local time;

[0011] The grid is divided according to the altitude range to which the orbit altitude of the satellite belongs, the altitude step, the latitude step and the local time step corresponding to the altitude range.

[0012] In some embodiments, the atmospheric density associated with the grid is obtained by sampling the location of the grid according to the space environment parameter interval;

[0013] The grid-associated space environment parameter intervals are classified according to solar activity levels and geomagnetic activity levels.

[0014] In some embodiments, the atmospheric density of the orbit where the satellite is located is obtained by interpolation correction based on the position, space environment parameter interval and atmospheric density associated with the adjacent grid, as well as the current position and the current space environment parameter.

[0015] In a second aspect, an embodiment of the present application provides a device for updating satellite ephemeris, the device comprising:

[0016] An acquisition module is used to obtain the current position of the satellite and the current space environment parameters;

[0017] A search module, used for searching a grid adjacent to the current position from a plurality of grids, wherein the grids are associated with the position, the space environment parameter interval and the atmospheric density;

[0018] The prediction module is used to predict the atmospheric density of the orbit where the satellite is located by using the position, space environment parameter interval and atmospheric density associated with the adjacent grid, as well as the current position and the current space environment parameter; and update the satellite's ephemeris by using the predicted atmospheric density.

[0019] In some embodiments, the association between the grid and the position, the space environment parameter interval and the atmospheric density is determined according to the orbital altitude and mission period of the satellite.

[0020] In some embodiments, the location includes altitude, latitude, and local time;

[0021] The grid is divided according to the altitude range to which the orbit altitude of the satellite belongs, the altitude step, the latitude step and the local time step corresponding to the altitude range.

[0022] In some embodiments, the atmospheric density associated with the grid is obtained by sampling the location of the grid according to the space environment parameter interval;

[0023] The grid-associated space environment parameter intervals are classified according to solar activity levels and geomagnetic activity levels.

[0024] In some embodiments, the prediction module is specifically used to:

[0025] Interpolation correction is performed based on the position, space environment parameter interval and atmospheric density associated with the adjacent grids as well as the current position and the current space environment parameter to obtain the atmospheric density of the orbit where the satellite is located.

[0026] In a third aspect, an embodiment of the present application provides a satellite-borne device, including a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus;

[0027] Memory, used to store computer programs;

[0028] The processor is used to implement any of the above-mentioned satellite ephemeris updating methods when executing the program stored in the memory.

[0029] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, it implements any of the above-mentioned satellite ephemeris updating methods.

[0030] In a fifth aspect, an embodiment of the present application further provides a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute any of the satellite ephemeris updating methods described above.

[0031] In the technical solution provided by the embodiment of the present application, information of multiple grids is pre-stored, such as position, space environment parameter interval, and atmospheric density, etc. In the case of limited computing power and storage of onboard equipment, the adjacent grids of the satellite's location can be quickly determined by checking the grids, and then the atmospheric density can be predicted based on the position, space environment parameter interval, and atmospheric density associated with the adjacent grids, and then the satellite's ephemeris can be quickly and accurately updated, achieving high-precision prediction of atmospheric density and high-precision prediction of satellite ephemeris in the case of limited computing power and storage of onboard equipment.

[0032] Of course, implementing any product or method of the present application does not necessarily require achieving all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application, and for ordinary technicians in this field, other embodiments can also be obtained based on these drawings.

[0034] Figure 1 A schematic diagram of a flow chart of a method for updating satellite ephemeris provided in an embodiment of the present application;

[0035] Figure 2 A schematic diagram of the atmospheric density grid file generation process provided in the embodiment of the present application;

[0036] Figure 3A schematic diagram of a satellite-based forecast application of atmospheric density prediction provided in an embodiment of the present application;

[0037] Figure 4 A schematic diagram of the structure of a device for updating satellite ephemeris provided in an embodiment of the present application;

[0038] Figure 5 A schematic diagram of the structure of a satellite-borne device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0039] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field based on the present application belong to the scope of protection of the present application.

[0040] The temporal and spatial variations of the thermospheric neutral atmosphere are complex, and the driving factors include external forcing forces of the thermospheric and ionosphere systems, internal dynamics of the thermospheric and ionosphere systems, and coupling between the thermosphere and the ionosphere. The temporal variation scale of the thermospheric neutral atmosphere ranges from sudden changes of a few minutes to hours, diurnal changes, multi-day changes, solar rotation changes, annual / half-year changes, solar cycle changes, and long-term trends on large time scales of several decades. The spatial variations of the thermospheric neutral atmosphere include changes in longitude and latitude, and changes in altitude. The vertical changes of the thermospheric neutral atmosphere decrease exponentially with altitude, and are also related to solar activity and geomagnetic activity, time, season, and longitude and latitude. There are many related factors that affect the changes in the thermospheric neutral atmosphere, and the prediction of atmospheric density is cumbersome and complex.

[0041] At present, there are two solutions for predicting the atmospheric density of satellite orbits. One is to predict the atmospheric density of satellite orbits on the ground. This solution uses an empirical thermosphere atmospheric model to predict the atmospheric density, and the calculation process is complex and time-consuming. The other is to predict the atmospheric density of satellite orbits on board. This solution uses a low-precision exponential atmospheric density model. Due to the limited computing power and storage of onboard equipment, it cannot meet the demand for high-precision atmospheric density prediction and the high-precision prediction demand of users for ephemeris.

[0042] To solve the above problems, the present application provides a method for updating satellite ephemeris, which can be applied to equipment mounted on a satellite, i.e., onboard equipment, or to ground equipment, without limitation. The above satellite ephemeris updating method includes the following steps: Figure 1 shown.

[0043] Step S11, obtaining the current position of the satellite and the current space environment parameters.

[0044] Step S12, searching for a grid adjacent to the current position from multiple grids, where the grid is associated with the position, the space environment parameter interval and the atmospheric density.

[0045] Step S13, using the position, space environment parameter interval and atmospheric density associated with the adjacent grids, as well as the current position and current space environment parameters, predict the atmospheric density of the orbit where the satellite is located.

[0046] Step S14, updating the satellite ephemeris using the predicted atmospheric density.

[0047] In the technical solution provided by the embodiment of the present application, information of multiple grids is pre-stored, such as position, space environment parameter interval, and atmospheric density, etc. In the case of limited computing power and storage of onboard equipment, the adjacent grids of the satellite's location can be quickly determined by checking the grids, and then the atmospheric density can be predicted based on the position, space environment parameter interval, and atmospheric density associated with the adjacent grids, and then the satellite's ephemeris can be quickly and accurately updated, achieving high-precision prediction of atmospheric density and high-precision prediction of satellite ephemeris in the case of limited computing power and storage of onboard equipment.

[0048] For ease of understanding, the following description is made with the satellite-borne equipment as the execution subject, which is not intended to be limiting.

[0049] In the above step S11, the current position is the position of the current satellite, which may include altitude, latitude, local time, etc. The current space environment parameters are the space environment parameters of the current satellite, which may include solar activity index and geomagnetic index, etc.

[0050] The solar activity index can be expressed as the solar radiation flux of a specified wavelength. The specified wavelength can be set according to actual needs. For example, the specified wavelength can be 10.7 centimeters (cm), and the solar activity index is the solar radiation flux of a wavelength of 10.7 cm. The solar activity index included in the current space environment parameters can be the solar radiation flux of the specified wavelength on the day, or the solar radiation flux of the specified wavelength in a preset time period centered on the current moment. Taking the specified wavelength of 10.7 cm as an example, the solar activity index included in the current space environment parameters can be the solar radiation flux of the wavelength of 10.7 cm on the day, or the solar radiation flux of the wavelength of 10.7 cm in a preset time period centered on the current moment.

[0051] The geomagnetic index may include one or more of the Kp index and the Ap index. The Kp index is the overall level of geomagnetic activity on a global scale; the Ap index is an index of the intensity of geomagnetic disturbances throughout the day on a global scale.

[0052] When broadcasting satellite ephemeris in ultra-real time, the onboard equipment can obtain the current position of the satellite and sample the space environment at the satellite's position to obtain the current space environment parameters.

[0053] In the above step S12, multiple grids are associated with positions, space environment parameter intervals and atmospheric density. The information associated with multiple grids can be stored in the form of a table, a database file, or other forms, which are not limited.

[0054] In the embodiment of the present application, the grid can be obtained by dividing in the following manner.

[0055] Method 1: You can divide the space according to the fixed height step, latitude step and local time step to obtain multiple grids corresponding to different heights. For example, according to the height step of 2 kilometers (km), the latitude step of 3 degrees (deg), and the local time step of 0.3 hours (h), you can divide the space to obtain multiple grids corresponding to different heights.

[0056] Method 2: The space environment can be classified according to the space environment response characteristics of atmospheric density at different orbital altitudes, that is, divided into multiple altitude ranges, and the altitude step, latitude step, and local time step corresponding to each altitude range are determined. For each altitude range, the space is divided according to the altitude step, latitude step, and local time step corresponding to the altitude range, and multiple grids corresponding to different altitudes are obtained. In other words, the grid can be obtained by dividing according to the altitude range to which the satellite's orbital altitude belongs, and the altitude step, latitude step, and local time step corresponding to the altitude range.

[0057] For example, the altitude area can be divided into four altitude range types: ultra-low area, low area, middle area and high area. The values ​​of each altitude range and the corresponding altitude step, latitude step and local time step of each altitude range are shown in Table 1.

[0058] Table 1

[0059] type Altitude range / km Height step / km Latitude / Local Time Step Ultra low area 100≤H≤200 2 3deg / 0.3h Low Zone 200<H≤350 3 5° / 0.5h Central District 350<H<500 5 10° / 0.8h High Area 500≤H≤1000 20 15° / 1h

[0060] In Table 1, H represents height. According to Table 1, multiple grids can be obtained.

[0061] In the embodiment of the present application, the corresponding height step, latitude step and local time step are adjusted according to the different height ranges, such as increasing the corresponding height step, latitude step and local time step as the height range increases. Because, as the height increases, the influence of various related factors on the spatiotemporal changes of the neutral atmosphere in the thermosphere decreases, therefore, as the height range increases, increasing the corresponding height step, latitude step and local time step reduces the number of grids, thereby reducing the storage requirements of grid-related information and improving grid generation efficiency.

[0062] After obtaining multiple grids, the position associated with each grid (i.e., the location of the grid) can be obtained, such as the altitude, latitude, and local time mentioned above. In addition, after obtaining multiple grids, the position associated with each grid can be sampled to obtain the atmospheric density associated with each grid under different space environment parameter intervals.

[0063] In the embodiment of the present application, in order to improve the accuracy of sampling to obtain atmospheric density, classification can be performed according to the solar activity level and the geomagnetic activity level to obtain multiple space environment parameter intervals, which can also be called sampling classifications; the location of the grid is sampled according to the space environment parameter interval to obtain the atmospheric density associated with each grid under different space environment parameter intervals. In the embodiment of the present application, the location, space environment parameter interval and atmospheric density associated with the grid are the grid values.

[0064] The solar activity cycle is 11 years. In the embodiment of the present application, the solar activity level can be determined according to the solar activity index, and the solar activity cycle can be divided according to the solar activity level to obtain multiple solar activity classifications; for each solar activity classification, the geomagnetic activity level can be determined according to the geomagnetic index, and the geomagnetic activity can be divided according to the geomagnetic activity level to obtain multiple geomagnetic activity classifications; and multiple space environment parameter intervals can be obtained by combining the solar activity classification and the geomagnetic activity classification.

[0065] For example, the solar activity index is the solar radiation flux at a wavelength of 10.7 cm, using F 10.7 Indicates that the solar activity level can be expressed as F, centered on the day 10.7 The sliding average of the specified time length is F' 10.7 Indicates that the geomagnetic activity level can be a geomagnetic index, such as the Kp index and the Ap index. The specified duration can be set according to actual needs, for example, the specified duration can be 81 days, 71 days, 61 days, etc. According to the solar activity level F' 10.7 The solar activity cycle is divided into three types of solar activity classification, namely high year, middle year and low year. The geomagnetic activity is divided according to the Kp index and the Ap index, namely five types of geomagnetic activity classification, namely geomagnetic calm, small magnetic storm, medium magnetic storm, large magnetic storm and strong magnetic storm, as shown in Table 2. Combining the three solar activity classifications and the five geomagnetic activity classifications, that is, under each solar activity classification, five geomagnetic activity classifications are further divided, a total of 15 space environment parameter intervals are obtained, as shown in Table 3.

[0066] Table 2

[0067] Classification of magnetic storm activity Kp Index Ap Index calm [0,5) [0,48) Small magnetic storm [5,6) [48,80) Moderate magnetic storm [6,7) [80,132) Big magnetic storm [7,8) [132,207) Strong magnetic storm [8,9] [207,400]

[0068] Table 3

[0069]

[0070]

[0071] Taking Table 2 and Table 3 as examples, the space environment parameter range can be expressed as: {solar activity classification, geomagnetic activity classification}, such as {F' 10.7 >150, the Kp index range is [0,5)}. The space environment parameter interval can also be expressed in other forms, such as {geomagnetic activity classification, solar activity classification}, etc.

[0072] In the embodiment of the present application, the above-mentioned space environment parameter intervals can also be divided more finely, such as the solar activity level corresponding to the high year is further divided into (150, 200], (200, 250, (250, ∞], etc.

[0073] After obtaining multiple space environment parameter intervals, a high-precision atmospheric density model can be used to sample each grid at different altitudes, solar activity levels, and geomagnetic activity levels to obtain the atmospheric density associated with each grid under different space environment parameter intervals. Afterwards, the grid values ​​of each sampled grid are encoded and classified to obtain one or more atmospheric density grid files, which are stored. The atmospheric density grid files store the grid values ​​of multiple grids.

[0074] In the embodiment of the present application, the above atmospheric density grid file generation process can be found in Figure 2 As shown, the following steps may be included.

[0075] Step S21, dividing the satellite orbit into altitude regions.

[0076] Step S22: Analyze the space environment response characteristics of atmospheric densities at different orbital altitudes and classify the space environment. The classification results can be seen in Table 1 above.

[0077] Step S23, using a high-precision atmospheric density model, sampling is performed at each grid at different altitudes, solar activity levels, and geomagnetic activity levels to obtain the atmospheric density associated with each grid at different space environment parameter intervals. The classification of solar activity levels and the classification of geomagnetic activity levels can be found in Tables 2 and 3 above.

[0078] Step S24, encoding and classifying the grid values ​​of each grid obtained by sampling, and obtaining an atmospheric density grid file corresponding to a high year, an atmospheric density grid file corresponding to a middle year, and an atmospheric density grid file corresponding to a low year.

[0079] Among them, the atmospheric density grid file corresponding to the high year stores the grid values ​​of different altitudes, different geomagnetic activity levels, and different grids in the high year; the atmospheric density grid file corresponding to the middle year stores the grid values ​​of different altitudes, different geomagnetic activity levels, and different grids in the middle year; the atmospheric density grid file corresponding to the low year stores the grid values ​​of different altitudes, different geomagnetic activity levels, and different grids in the low year.

[0080] The above atmospheric density grid file generation process can be completed by ground equipment or by satellite equipment. Assume that the above atmospheric density grid file generation process can be completed by ground equipment. Before performing atmospheric density prediction, the ground equipment can inject all generated atmospheric density grid files into the satellite equipment, and the satellite equipment decodes the obtained atmospheric density grid files into the relationship between the grid and the position, the space environment parameter interval and the atmospheric density, and then completes the storage of the grid and the grid-related information.

[0081] In order to save the storage resources of onboard equipment and meet the demand for atmospheric density prediction when the storage of onboard equipment is limited, ground equipment can select the atmospheric density grid file that needs to be injected into the onboard equipment according to the satellite's orbital altitude and mission cycle; and then inject the selected atmospheric density grid file into the onboard equipment, and the onboard equipment decodes the obtained atmospheric density grid file into the correlation between the grid and the position, the space environment parameter interval and the atmospheric density.

[0082] The ground equipment can obtain the orbital altitude and mission period of the satellite from the mission design of the satellite. For example, the mission design: the orbital altitude is 510km, and the mission period is the solar high year. Based on the orbital altitude and mission period in the mission design, an atmospheric density grid file consisting of grid values ​​of multiple grids in the high year and altitude range of 480-550km can be selected; the selected atmospheric density grid file is injected into the onboard equipment.

[0083] After obtaining the association between the grid and the position, the space environment parameter range and the atmospheric density, the onboard equipment can search for the adjacent grids of the current position of the satellite in the grid. The adjacent grids can include six grids: up, down, left, right, front and back.

[0084] In the above step S13, the onboard device obtains the grid value of the adjacent grid, and then determines the position corresponding to the adjacent grid based on the grid value of the adjacent grid, and obtains the space environment parameter interval to which the current space environment parameter belongs, and the atmospheric density in the space environment parameter interval from the grid value of the adjacent grid. The onboard device predicts the atmospheric density of the orbit where the satellite is located by using the position corresponding to the adjacent grid, the atmospheric density in the space environment parameter interval to which the current space environment parameter belongs, and the current position and the current space environment parameter.

[0085] In some embodiments, the atmospheric density of the orbit where the satellite is located is obtained by interpolation correction based on the position associated with the adjacent grid, the space environment parameter interval and the atmospheric density, as well as the current position and the current space environment parameter. That is, the onboard device can perform interpolation correction based on the position associated with the adjacent grid, the space environment parameter interval and the atmospheric density, as well as the current position and the current space environment parameter to obtain the atmospheric density of the orbit where the satellite is located.

[0086] For example, onboard equipment can use the following formula for interpolation correction to obtain the atmospheric density of the satellite's orbit.

[0087]

[0088]

[0089] S(F 10.7 , Kp)=0.0012ΔF 10.7 +0.0028ΔKp

[0090] In the above formula, ρ represents the atmospheric density of the satellite's orbit, ρ 0 Represents the atmospheric density of the neighboring grid above the current position, ρ 1 Indicates the atmospheric density of the adjacent grid below the current position, h 0 Indicates the height of the adjacent grid above the current position, h 1 represents the height of the adjacent grid below the current position, h represents the height of the current satellite position, H represents the standard height, e represents the natural constant, S(F 10.7 ,Kp) represents the correction function of solar radiation flux and geomagnetic index, represents the correction function of latitude and local time, Indicates the satellite position and latitude direction The latitude difference, and Indicates the latitude of two adjacent grids in the latitude direction, Δt L t represents the satellite position and local time direction L1 The local time difference, t L1 and t L2 Indicates the local time direction of two adjacent grids, t L2 >t L1 , Represents the density difference between two adjacent grids in the latitude direction, Δρ tL Indicates the density difference between two adjacent grids in the local time direction, ΔF 10.7 Indicates the maximum F of the space environment parameter interval to which the current space environment parameter belongs 10.7 and minimum F 10.7, ΔKp represents the difference between the maximum Kp and the minimum Kp of the space environment parameter interval to which the current space environment parameter belongs.

[0091] In the embodiment of the present application, the satellite-borne equipment uses the above formula to predict the atmospheric density, simplifies the correction formula, avoids the use of exponential and logarithmic operations as much as possible, and reduces the computing power required for atmospheric density prediction.

[0092] In the embodiments of the present application, the satellite-borne equipment may also use other interpolation algorithms, such as linear interpolation algorithms and nonlinear interpolation algorithms, to predict the atmospheric density, which is not limited.

[0093] In the technical solution provided in the embodiment of the present application, the satellite-borne device uses the adjacent grid to correct the current position and current space environment parameters of the satellite-borne device, and uses the corrected position and the corrected space environment parameters to predict the atmospheric density, thereby improving the accuracy of the atmospheric density prediction.

[0094] In the above step S14, after the atmospheric density is predicted, the satellite-borne device can use the predicted atmospheric density to predict the position of the satellite in the future, and then update the satellite's ephemeris. After updating the satellite's ephemeris, the satellite-borne device can broadcast the updated ephemeris, that is, the ultra-real-time forecast ephemeris. After the user receives the ephemeris, the ephemeris is interpolated to obtain the navigation position at the time of receiving the ephemeris, and finally the user's own positioning information is obtained by solving.

[0095] Combine the following Figure 3 The schematic diagram of the satellite-based forecast application of atmospheric density prediction shown in the figure provides a detailed description of the atmospheric density prediction method provided in the embodiment of the present application.

[0096] Step S31: ground equipment obtains the solar activity cycle.

[0097] Step S32: the ground equipment obtains the mission design of the satellite.

[0098] The execution order of step S31 and step S32 is not limited in the embodiment of the present application.

[0099] Step S33: The ground device selects an atmospheric density grid file according to the solar activity cycle and the mission design, and injects the selected atmospheric density grid file into the onboard device. The onboard device generates a lookup table according to the injected atmospheric density grid file.

[0100] Step S34, the onboard equipment looks up a table, performs interpolation correction calculations, and predicts the atmospheric density.

[0101] Step S35: The satellite-borne equipment performs ephemeris prediction based on the predicted atmospheric density.

[0102] The satellite-borne equipment broadcasts the ephemeris in ultra-real time according to the atmospheric density. After the user receives the ephemeris, the ephemeris is interpolated to obtain the navigation position at the time of receiving the ephemeris signal, and finally the user's own positioning information is solved.

[0103] In the technical solution provided in the embodiment of the present application, by injecting an atmospheric density grid file that matches the mission design, the onboard equipment can improve the information query efficiency of the predicted atmospheric density while reducing storage requirements, thereby achieving high-precision prediction of atmospheric density under limited computing power and storage after the satellite enters orbit, thereby ensuring the accuracy of ultra-real-time ephemeris forecasts and providing users with stable, high-precision navigation and positioning services.

[0104] Corresponding to the above-mentioned satellite ephemeris updating method, the present application embodiment also provides a satellite ephemeris updating device, such as Figure 4 As shown, the device comprises:

[0105] An acquisition module 41 is used to acquire the current position of the satellite and the current space environment parameters;

[0106] A search module 42, configured to search a plurality of grids for a neighboring grid of the current position, wherein the grids are associated with the position, the space environment parameter interval and the atmospheric density;

[0107] The prediction module 43 is used to predict the atmospheric density of the orbit where the satellite is located by using the position, space environment parameter interval and atmospheric density associated with the adjacent grids, as well as the current position and the current space environment parameters; and update the satellite's ephemeris using the predicted atmospheric density.

[0108] In some embodiments, the association between the grid and the position, the space environment parameter interval and the atmospheric density is determined according to the orbital altitude and mission period of the satellite.

[0109] In some embodiments, the location includes altitude, latitude, and local time;

[0110] The grid is divided according to the altitude range to which the satellite's orbit altitude belongs, the altitude step corresponding to the altitude range, the latitude step and the local time step.

[0111] In some embodiments, the atmospheric density associated with the grid is obtained by sampling the location of the grid according to the space environment parameter interval;

[0112] The grid-associated space environment parameter intervals are classified according to solar activity levels and geomagnetic activity levels.

[0113] In some embodiments, the prediction module 43 can be specifically used to perform interpolation correction based on the position, space environment parameter interval and atmospheric density associated with the adjacent grids as well as the current position and the current space environment parameters to obtain the atmospheric density of the orbit where the satellite is located.

[0114] In the technical solution provided in the embodiment of the present application, information of multiple grids, such as position, space environment parameters, and atmospheric density, is stored in a preset lookup table. When the onboard computing power and storage are limited, the neighboring grids of the satellite's location can be quickly determined by looking up the table, and then the atmospheric density can be quickly and accurately predicted based on the position, space environment parameters, and atmospheric density corresponding to the neighboring grids, thus achieving high-precision prediction of atmospheric density when the onboard computing power and storage are limited.

[0115] Corresponding to the above-mentioned satellite ephemeris updating method, the present application embodiment also provides a satellite-borne device, such as Figure 5 As shown, it includes a processor 51, a communication interface 52, a memory 53 and a communication bus 54, wherein the processor 51, the communication interface 52, and the memory 53 communicate with each other through the communication bus 54;

[0116] A memory 53, for storing computer programs;

[0117] The processor 51 is used to implement any of the above-mentioned satellite ephemeris updating methods when executing the program stored in the memory 53.

[0118] The communication bus mentioned in the above-mentioned satellite-borne equipment can be a Peripheral Component Interconnect (PCI) bus or an Extended Industry Standard Architecture (EISA) bus, etc. The communication bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, only one thick line is used in the figure, but it does not mean that there is only one bus or one type of bus.

[0119] The communication interface is used for communication between the above-mentioned onboard equipment and other equipment.

[0120] The memory may include a random access memory (RAM) or a non-volatile memory (NVM), such as at least one disk memory. Optionally, the memory may also be at least one storage device located away from the aforementioned processor.

[0121] The above-mentioned processor can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0122] In another embodiment provided in the present application, a computer-readable storage medium is provided, in which a computer program is stored. When the computer program is executed by a processor, any of the satellite ephemeris updating methods described above is implemented.

[0123] In another embodiment provided by the present application, a computer program product including instructions is also provided, which, when executed on a computer, enables the computer to execute any of the satellite ephemeris updating methods described above.

[0124] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on a computer, the process or function described in the embodiment of the present application is generated in whole or in part. The computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer 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 instructions may be transmitted from a website site, computer, server or data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) mode to another website site, computer, server or data center. The computer-readable storage medium may be any available medium that a computer can access or a data storage device such as a server or data center that includes one or more available media integrated. The available medium may be a magnetic medium, (e.g., a floppy disk, a hard disk, a tape), an optical medium (e.g., a DVD), or a semiconductor medium (e.g., a solid-state drive Solid State Disk (SSD)), etc.

[0125] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0126] Each embodiment in this specification is described in a related manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device, onboard equipment, storage medium and computer program product embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiments.

[0127] The above description is only a preferred embodiment of the present application and is not intended to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application are included in the protection scope of the present application.

Claims

1. A method for updating satellite ephemeris, characterized in that: The method comprises: Get the current position of the satellite and the current space environment parameters; Searching for a neighboring grid of the current position from a plurality of grids, wherein the grid is associated with a position, a space environment parameter interval, and an atmospheric density; Predicting the atmospheric density of the orbit where the satellite is located by using the position, space environment parameter interval and atmospheric density associated with the adjacent grids, as well as the current position and the current space environment parameter; The predicted atmospheric density is used to update the satellite's ephemeris.

2. The method according to claim 1, characterized in that The correlation between the grid and the position, the space environment parameter interval and the atmospheric density is determined according to the orbital altitude and mission period of the satellite.

3. The method according to claim 1, characterized in that The position includes altitude, latitude and local time; The grid is divided according to the altitude range to which the orbit altitude of the satellite belongs, the altitude step, the latitude step and the local time step corresponding to the altitude range.

4. The method according to claim 1, characterized in that: The atmospheric density associated with the grid is obtained by sampling the location of the grid according to the spatial environment parameter interval; The grid-associated space environment parameter intervals are classified according to solar activity levels and geomagnetic activity levels.

5. The method according to any one of claims 1 to 4, characterized in that: The atmospheric density of the orbit where the satellite is located is obtained by interpolation correction based on the position, space environment parameter interval and atmospheric density associated with the adjacent grids, as well as the current position and the current space environment parameters.

6. A satellite ephemeris updating device, characterized in that: The device comprises: An acquisition module is used to obtain the current position of the satellite and the current space environment parameters; A search module, used for searching a grid adjacent to the current position from a plurality of grids, wherein the grids are associated with the position, the space environment parameter interval and the atmospheric density; The prediction module is used to predict the atmospheric density of the orbit where the satellite is located by using the position, space environment parameter interval and atmospheric density associated with the adjacent grid, as well as the current position and the current space environment parameter; and update the satellite's ephemeris by using the predicted atmospheric density.

7. The device according to claim 6, characterized in that The correlation between the grid and the position, the space environment parameter interval and the atmospheric density is determined according to the orbital altitude and mission period of the satellite.

8. The device according to claim 6, characterized in that The position includes altitude, latitude and local time; The grid is obtained by dividing according to the altitude range to which the orbit altitude of the satellite belongs, the altitude step length, the latitude step length and the local time step length corresponding to the altitude range; The atmospheric density associated with the grid is obtained by sampling the location of the grid according to the spatial environment parameter interval; The grid-associated space environment parameter intervals are classified according to solar activity levels and geomagnetic activity levels.

9. The device according to any one of claims 6 to 8, characterized in that: The prediction module is specifically used for: Interpolation correction is performed based on the position, space environment parameter interval and atmospheric density associated with the adjacent grids as well as the current position and the current space environment parameter to obtain the atmospheric density of the orbit where the satellite is located.

10. A satellite-borne device, characterized in that: It includes a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory communicate with each other through the communication bus; Memory, used to store computer programs; A processor, for implementing the method steps described in any one of claims 1 to 5 when executing a program stored in a memory.

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