Attenuation rate calculation method and system, attenuation rate adjustment method and system, equipment and medium

Abstract

The invention relates to the technical field of satellite orbit calculation, and provides an attenuation rate calculation method and system, an attenuation rate adjustment method and system, equipment and a medium. Comprising the following steps: S1, acquiring the current orbit height of the sun synchronous satellite; s2, determining a data acquisition time period according to the current orbit height; s3, collecting the track height data in the data collection time period from the current moment; s4, fitting the collected orbit height data into a linear decreasing straight line, and obtaining a straight line formula; and S5, calculating the attenuation rate of the sun synchronous satellite according to a linear formula. According to the scheme, the attenuation rate of the sun synchronous satellite can be accurately calculated, and the orbit height of the satellite can be timely adjusted, so that the satellite can more effectively execute tasks.

Description

Technical Field

[0001] The present invention relates to the field of satellite orbit calculation technology, and in particular to an attenuation rate calculation method and system, an adjustment method and system, a device and a medium. Background Art

[0002] A sun-synchronous satellite is a satellite that orbits in a sun-synchronous orbit. The satellite orbit plane passes through the Earth's North and South Poles and moves eastward by 0.9856 degrees every day. This angle is exactly the angle that the Earth moves eastward every day when it orbits the sun. Sun-synchronous satellites have the following characteristics: First, timed observation: Sun-synchronous satellites enable satellites to pass through specific ground points at fixed time intervals. This is very important for tasks that require timed observation, such as earth observation, meteorological monitoring, ocean monitoring, etc. The time it takes for a sun-synchronous satellite to pass over the earth is almost the same each time, which makes the observation data more comparable and facilitates long-term trend analysis and time series observation.

[0003] Second, global coverage: Sun-synchronous orbits enable continuous observation coverage of the Earth's global range. Due to the characteristics of the orbit, the orbital inclination of sun-synchronous satellites is usually close to 90 degrees, allowing the satellite to cover approximately the same longitude range each time it enters the Earth's hemisphere, achieving balanced observation of different regions of the Earth.

[0004] Third, sunlight conditions: The sun-synchronous orbit ensures that the satellite has similar sunlight conditions above the earth. The orbital inclination and altitude of the sun-synchronous satellite are precisely designed so that the satellite can receive similar sunlight in different seasons and different locations, maintaining consistent lighting conditions, making the observation data more stable and reliable.

[0005] Fourth, communication and data transmission: The time and position of the sun-synchronous orbit above the earth are relatively fixed, which facilitates the communication and data transmission between the satellite and the ground station. This enables the satellite to transmit observation data, control instructions and status information in a timely manner, ensuring the normal collection and processing of data.

[0006] Therefore, choosing a sun-synchronous orbit for many low-orbit satellites can provide stable observation conditions and data continuity, enabling the satellite to perform its mission more effectively.

[0007] Satellites are affected by a variety of perturbations during their orbital motion, which may cause the orbit to deviate and change. Common perturbations include the non-spherical perturbation of the Earth, the gravitational force of the Sun and the Moon, atmospheric drag, solar light pressure, tidal force, etc. Sun-synchronous satellites are mainly affected by the non-spherical perturbations of the Earth and atmospheric drag, which cause the orbital altitude to continue to decrease. Especially in years with high solar activity, the satellite decays faster. The stability of the orbit is crucial to satellite missions such as communication, observation, and navigation. If the satellite decay rate exceeds the expected range, orbit control methods need to be used to keep the satellite on the correct orbit. Therefore, it is very important to know the decay rate of sun-synchronous satellites. By analyzing the decay rate, it is possible to predict the resources that the satellite may need in the future, such as fuel, power, and transmission bandwidth, which helps to optimize resource allocation and ensure the sustainable development of the satellite system.

[0008] The existing technology usually directly uses the instantaneous root or square root semi-major axis of the satellite at the beginning and end of a period of time to subtract, and then divides by the interval of time to obtain the satellite's daily attenuation. The shortcomings of this calculation method are as follows: First, the difference between the flat root and the instantaneous root is that the flat root takes into account the influence of the perturbation force on the orbit. Since the flat root eliminates short-term changes and only considers long-term changes, it reflects the long-term change trend of the orbit and greatly simplifies the orbit perturbation analysis. Therefore, the flat root should be used to calculate the orbital altitude of the satellite.

[0009] Second, since the orbit fluctuates, the attenuation rate obtained by directly subtracting the semi-major axis at the beginning and end of a certain time period of the satellite is less accurate, ignores the intermediate fluctuations, and cannot fully reflect the changes in the data.

[0010] Therefore, it is necessary to provide a decay rate calculation method and system, an adjustment method and system, a device and a medium to accurately calculate the decay rate of a sun-synchronous satellite and timely adjust the satellite orbit altitude so that the satellite can perform its mission more effectively.

[0011] The above information disclosed in the Background section is only for enhancement of understanding of the background of the present application and therefore it may contain information that does not constitute the prior art that is already known to a person of ordinary skill in the art. Summary of the invention

[0012] The main purpose of the present invention is to overcome the problem of inaccurate calculation of the attenuation rate of a sun-synchronous satellite, and to provide a method and system for calculating the attenuation rate, an adjustment method and system, a device and a medium to accurately calculate the attenuation rate of a sun-synchronous satellite and timely adjust the satellite orbit altitude so that the satellite can perform its mission more effectively.

[0013] To achieve the above-mentioned purpose, the first aspect of the present invention provides a method for calculating the attenuation rate of a sun-synchronous satellite, comprising the following steps: S1: Get the current orbital altitude of the sun-synchronous satellite; S2: Determine a data collection period according to the current orbit altitude; S3: starting from the current moment, collecting orbital height data within the data collection period; S4: Fitting the collected orbital height data into a linearly decreasing straight line and obtaining a straight line formula; S5: Calculate the attenuation rate of the sun-synchronous satellite according to the straight-line formula.

[0014] According to a specific embodiment of the present invention, a sun-synchronous satellite is a satellite operating in a sun-synchronous orbit, which revolves around the earth, and the satellite orbit plane passes through the north and south poles of the earth and moves eastward by 0.9856 degrees every day. This angle is exactly the angle of the earth's eastward movement every day when it revolves around the sun.

[0015] According to a specific embodiment of the present invention, step S1 further includes: if the current orbit altitude is higher than or equal to 300 km and not higher than 6000 km, then proceed to step S2, otherwise the attenuation rate calculation is abandoned.

[0016] The inclination of a sun-synchronous orbit must be greater than 90°, that is, it is a retrograde orbit. In a circular orbit, the maximum inclination is 180°, so the height of a sun-synchronous orbit will not exceed 6000km. The lower the orbit altitude, the greater the atmospheric drag, and the faster the semi-major axis decays. For satellites below 300km orbit altitude, the calculated attenuation fluctuates greatly every day, so it is not analyzed. Under the condition that the space environment is stable and the satellite is not maneuvering, data of about half a month can be selected for analysis. If there are more active solar activities such as geomagnetic storms during this period, the data needs to be removed before analysis.

[0017] According to a specific embodiment of the present invention, in step S3, collecting the orbital height data within the data collection period starting from the current moment includes: collecting the orbital height data within the data collection duration starting from the current moment at specified time intervals; the specified time is not less than 1 minute and not more than 1 hour.

[0018] According to a specific embodiment of the present invention, in step S4, fitting the collected orbital altitude data into a linearly decreasing straight line includes: adopting a linear regression fitting method.

[0019] Sun-synchronous orbit satellites are mainly affected by the non-spherical perturbation of the earth and atmospheric drag, which makes the orbit altitude basically show a linear decay trend over a period of time. Therefore, the linear regression fitting method is adopted. The basic idea is to find a straight line that can best describe the relationship between data points. Specifically, the goal of linear regression is to find a straight line that minimizes the sum of the vertical distances from all data points to this line.

[0020] According to a specific embodiment of the present invention, in step S5, the attenuation rate of the sun-synchronous satellite is calculated according to the straight line formula, including: The straight line formula includes a slope, and the attenuation rate of the sun-synchronous satellite is obtained according to the slope; The method of obtaining the attenuation rate of a sun-synchronous satellite according to the slope includes: obtaining the attenuation of the semi-major axis of the satellite orbit per minute according to the slope, and calculating the attenuation of the semi-major axis of the satellite orbit per day according to the attenuation of the semi-major axis of the satellite orbit per minute, that is, the attenuation rate of the sun-synchronous satellite.

[0021] As a second aspect of the present invention, a decay rate calculation system applicable to a sun-synchronous satellite is provided, comprising: The current orbit altitude module is used to obtain the current orbit altitude of the sun-synchronous satellite; A time period determination module, communicatively connected to the current orbit height acquisition module, for determining a data collection time period according to the current orbit height; A collection module, communicatively connected to the time period determination module and the current orbit height acquisition module, for collecting orbit height data within the data collection time period starting from the current moment; A fitting module, communicatively connected to the acquisition module, for fitting the acquired orbit height data into a linearly decreasing straight line and obtaining a straight line formula; The attenuation rate calculation module is communicatively connected with the fitting module and is used to calculate the attenuation rate of the sun-synchronous satellite according to the straight line formula.

[0022] As a third aspect of the present invention, the present invention provides an altitude adjustment method applicable to a sun-synchronous satellite, comprising the following steps: Calculating the attenuation rate of the sun-synchronous satellite according to the attenuation rate calculation method applicable to the sun-synchronous satellite; The semi-major axis increment and time interval required for adjusting the satellite trajectory are determined according to the attenuation rate; and the orbit of the satellite is adjusted according to the semi-major axis increment and time interval required for adjusting the satellite trajectory.

[0023] As an example implementation of the present invention, the satellite trajectory is adjusted to the east of the nominal trajectory. The semi-major axis increment required for adjustment is 2△a, and the adjustment time interval is ; Among them, △λ represents the maximum value of the satellite sub-satellite point trajectory drift, that is, the geographic longitude range of the satellite actual sub-satellite point trajectory relative to the nominal trajectory is ± ; △a represents the semi-major axis increment required to control the satellite sub-satellite point trajectory to the nominal trajectory when it drifts to the eastern boundary; Represents the decay rate of the semi-major axis of the satellite orbit.

[0024] As a fourth aspect of the present invention, the present invention provides an altitude adjustment system applicable to a sun-synchronous satellite, characterized in that it comprises: the attenuation rate calculation system applicable to a sun-synchronous satellite and an altitude adjustment module; The altitude adjustment module is used to determine the semi-major axis increment and time interval required to adjust the satellite trajectory according to the attenuation rate of the sun-synchronous satellite calculated by the attenuation rate calculation system applicable to the sun-synchronous satellite; and adjust the orbit of the satellite according to the semi-major axis increment and time interval required to adjust the satellite trajectory.

[0025] As a fifth aspect of the present invention, the present invention provides an electronic device, comprising: one or more processors; A storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the attenuation rate calculation method applicable to a sun-synchronous satellite.

[0026] As a sixth aspect of the present invention, the present invention provides a computer-readable medium having a computer program stored thereon, and when the program is executed by a processor, the attenuation rate calculation method applicable to a sun-synchronous satellite is implemented.

[0027] The advantages of the present invention are: The method of the present invention calculates the satellite orbit position within a predetermined time range through a fitting method, accurately calculates the attenuation rate of the sun-synchronous satellite, and timely adjusts the satellite orbit altitude, so that the satellite can perform its mission more effectively. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and other objects, features and advantages of the present application will become more apparent by describing in detail the exemplary embodiments thereof with reference to the accompanying drawings. The accompanying drawings described below are only some embodiments of the present application, and it is clear to a person skilled in the art that other accompanying drawings can be obtained from these accompanying drawings without creative effort.

[0029] Figure 1 The figure schematically shows a step diagram of a method for adjusting the altitude of a sun-synchronous satellite.

[0030] Figure 2 The diagram schematically shows the changing trend of the semi-major axis of the sun-synchronous satellite orbit.

[0031] Figure 3 A comparison diagram of the calculated decay rate and the actual track height according to a specific embodiment is schematically shown.

[0032] Figure 4 A schematic diagram of the sub-satellite point trajectory control loop is schematically shown.

[0033] Figure 5 A block diagram of an electronic device is schematically shown.

[0034] Figure 6 A block diagram of a computer-readable medium is schematically shown. DETAILED DESCRIPTION

[0035] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this application will be comprehensive and complete and will fully convey the concepts of the example embodiments to those skilled in the art. The same reference numerals in the figures represent the same or similar parts, and thus their repeated description will be omitted.

[0036] In addition, described feature, structure or characteristic can be combined in one or more embodiments in any suitable manner. In the following description, many specific details are provided to provide a full understanding of the embodiments of the present application. However, those skilled in the art will appreciate that the technical scheme of the present application can be put into practice without one or more of the specific details, or other methods, components, devices, steps, etc. can be adopted. In other cases, known methods, devices, realizations or operations are not shown or described in detail to avoid blurring the various aspects of the application.

[0037] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities may be implemented in software form, or in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0038] The flowcharts shown in the accompanying drawings are only exemplary and do not necessarily include all the contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps can be decomposed, and some operations / steps can be combined or partially combined, so the actual execution order may change according to actual conditions.

[0039] It should be understood that although the terms first, second, third, etc. may be used herein to describe various components, these components should not be limited by these terms. These terms are used to distinguish one component from another component. Therefore, the first component discussed below can be referred to as the second component without departing from the teachings of the concepts of the present application. As used herein, the term "and / or" includes any one of the associated listed items and all combinations of one or more.

[0040] Those skilled in the art will appreciate that the drawings are merely schematic diagrams of example embodiments, and the modules or processes in the drawings are not necessarily necessary for implementing the present application, and therefore cannot be used to limit the scope of protection of the present application.

[0041] According to a first specific embodiment of the present invention, the present invention provides a decay rate calculation system applicable to a sun-synchronous satellite, comprising: The current orbit altitude module is used to obtain the current orbit altitude of the sun-synchronous satellite; A time period determination module, communicatively connected to the current orbit height acquisition module, for determining a data collection time period according to the current orbit height; A collection module, communicatively connected to the time period determination module and the current orbit height acquisition module, for collecting orbit height data within the data collection time period starting from the current moment; A fitting module, communicatively connected to the acquisition module, for fitting the acquired orbit height data into a linearly decreasing straight line and obtaining a straight line formula; The attenuation rate calculation module is communicatively connected with the fitting module and is used to calculate the attenuation rate of the sun-synchronous satellite according to the straight line formula.

[0042] According to a second specific embodiment of the present invention, a method for calculating a decay rate applicable to a sun-synchronous satellite is provided, using the decay rate calculation system of the first specific embodiment, comprising the following steps: S1: Get the current orbital altitude of the sun-synchronous satellite.

[0043] A sun-synchronous satellite is a satellite that orbits the Earth in a sun-synchronous orbit. The satellite orbital plane passes through the Earth's North and South Poles and moves eastward by 0.9856 degrees every day. This angle is exactly the angle that the Earth moves eastward every day when it revolves around the sun.

[0044] Step S1 also includes: if the current orbit altitude is higher than or equal to 300 km and not higher than 6000 km, proceed to step S2, otherwise abandon the attenuation rate calculation.

[0045] The inclination of a sun-synchronous orbit must be greater than 90°, that is, it is a retrograde orbit. In a circular orbit, the maximum inclination is 180°, so the height of a sun-synchronous orbit will not exceed 6000km. The lower the orbit altitude, the greater the atmospheric drag, and the faster the semi-major axis decays. For satellites below 300km orbit altitude, the calculated attenuation fluctuates greatly every day, so it is not analyzed. Under the condition that the space environment is stable and the satellite is not maneuvering, data of about half a month can be selected for analysis. If there are more active solar activities such as geomagnetic storms during this period, the data needs to be removed before analysis.

[0046] S2: Determine a data collection period according to the current orbit altitude.

[0047] S3: Collecting orbital height data within the data collection period starting from the current moment.

[0048] The collecting of the orbit height data within the data collection period from the current moment includes: collecting the orbit height data within the data collection duration from the current moment at specified time intervals; the specified time is not less than 1 minute and not more than 1 hour. The specified time mainly depends on the data collection duration, and the more data points, the better.

[0049] S4: Fit the collected orbital height data into a linearly decreasing straight line and obtain the straight line formula.

[0050] The step of fitting the collected orbital height data into a linearly decreasing straight line includes: adopting a linear regression fitting method.

[0051] Satellites are affected by a variety of perturbations during their orbital motion, which may cause the orbit to deviate and change. Common perturbations include the non-spherical perturbation of the earth, the gravitational force of the sun and the moon, atmospheric drag, solar pressure, tidal force, etc. There are two types of representations of satellite orbits: instantaneous root and flat root. The instantaneous root refers to the orbital element of the satellite at a certain moment, which describes the position and velocity of the satellite at that moment. The flat root refers to the average element obtained by averaging the satellite orbit, which describes the average properties of the satellite orbit. The difference between the flat root and the instantaneous root is that the influence of the perturbation on the orbit is taken into account. Since the flat root eliminates short-period changes and only considers long-term changes, it reflects the long-term change trend of the orbit and greatly simplifies the analysis of orbital perturbations. Therefore, the flat root is often used to analyze the orbit of the satellite.

[0052] Figure 2 The variation trend of the semi-major axis of the orbit of the sun-synchronous satellite at three different orbital altitudes and different descending node locations is analyzed. Among them, line 1 represents the sun-synchronous orbit satellite with a semi-major axis of 600km, line 2 represents the sun-synchronous orbit satellite with a semi-major axis of 550km, and line 3 represents the sun-synchronous orbit satellite with a semi-major axis of 500km. Through observation, it can be seen that the sun-synchronous satellite is mainly affected by the non-spherical perturbation of the earth and the atmospheric drag, which makes the orbital altitude show a linear decay trend.

[0053] Sun-synchronous orbit satellites are mainly affected by the non-spherical perturbation of the earth and atmospheric drag, which makes the orbit altitude basically show a linear decay trend over a period of time. Therefore, the linear regression fitting method is adopted. The basic idea is to find a straight line that can best describe the relationship between data points. Specifically, the goal of linear regression is to find a straight line that minimizes the sum of the vertical distances from all data points to this line.

[0054] The orbital semi-major axis of a period of time is fitted into a linear decreasing line and the straight line formula is expressed. The slope, intercept and other information are obtained from the fitting results to further analyze the characteristics and laws of the data and calculate the daily attenuation of the satellite. This method can better reflect the overall trend and changes of the data. It uses multiple data points for calculation, which is more comprehensive than the method of only considering the difference between the first and last two points.

[0055] S5: Calculate the attenuation rate of the sun-synchronous satellite according to the straight-line formula.

[0056] In step S5, the attenuation rate of the sun-synchronous satellite is calculated according to the straight line formula, including: The straight line formula includes a slope, and the attenuation rate of the sun-synchronous satellite is obtained according to the slope; The method of obtaining the attenuation rate of a sun-synchronous satellite according to the slope includes: obtaining the attenuation of the semi-major axis of the satellite orbit per minute according to the slope, and calculating the attenuation of the semi-major axis of the satellite orbit per day according to the attenuation of the semi-major axis of the satellite orbit per minute, that is, the attenuation rate of the sun-synchronous satellite.

[0057] Fitting is to connect a series of points on a plane with a smooth curve. Since the orbit height of a sun-synchronous satellite decays approximately linearly, the semi-major axis of the sun-synchronous satellite's orbit is fitted into a linear straight line represented by a linear function of one variable, in the format of y=kx+b, where k is the decay rate. The daily decay of the satellite orbit can be calculated based on the decay rate.

[0058] The inclination of a sun-synchronous satellite is about 90 degrees, which will cause the orbit to decay in a linear trend. However, due to the greater influence of the non-spherical perturbation of the earth, the orbit of a low-orbit satellite with medium and low inclination angles fluctuates and decays periodically. The calculation method of the decay rate of other near-Earth satellites (low-orbit satellites with medium and low inclination angles) cannot be directly applied to the calculation method of the decay rate of sun-synchronous satellites. For low-orbit satellites, the lower the orbit altitude, the greater the atmospheric resistance, the faster the satellite decays, and the greater the slope.

[0059] The slope obtained from the fitting is the decay rate of the semi-major axis of the satellite orbit.

[0060] Assume that the linear expression obtained by fitting 1000 satellite orbit semi-major axis data at 1 minute intervals is y=-0.088x+6378110 (y-axis unit: meter, x-axis unit: minute). This linear expression means that the satellite orbit semi-major axis decays by 0.088 meter per minute, that is, the satellite orbit semi-major axis decay rate is 0.088 (meters / minute)*24 (hours / day)*60 (minutes / hour)=126.72 (meters / day).

[0061] like Figure 3As shown in the figure below, the orbital change of a sun-synchronous satellite at an orbital altitude of 500 km in 100 days is shown as the scattered point curve of line 1 in the figure below. By fitting the scattered points, we can get Figure 3 The dotted line 2 is the overall attenuation of the satellite. According to the trend formula of orbital attenuation, y=-0.0127x+6870.2 (x-axis unit hr, y-axis unit km), the average daily attenuation is calculated to be 0.3048km. If the previous method of calculating the orbital attenuation rate is used, the average daily attenuation is 0.2938km, which is 0.011km away from the result of the present invention. In addition, by comparing the actual orbit with the fitted orbit, the changes in the space environment and the impact of external factors on the satellite orbit can be analyzed.

[0062] The method of the present invention calculates the satellite orbit position within a predetermined time range through a fitting method, accurately calculates the attenuation rate of the sun-synchronous satellite, and timely adjusts the satellite orbit altitude, so that the satellite can perform its mission more effectively.

[0063] After obtaining the attenuation rate of the sun-synchronous satellite, the orbital altitude of the sun-synchronous satellite can be adaptively adjusted according to the attenuation rate.

[0064] According to a third specific embodiment of the present invention, the present invention provides an altitude adjustment system applicable to a sun-synchronous satellite, characterized in that it comprises: the attenuation rate calculation system applicable to a sun-synchronous satellite of the first specific embodiment and an altitude adjustment module; The altitude adjustment module is used to determine the semi-major axis increment and time interval required to adjust the satellite trajectory according to the attenuation rate of the sun-synchronous satellite calculated by the attenuation rate calculation system applicable to the sun-synchronous satellite; and adjust the orbit of the satellite according to the semi-major axis increment and time interval required to adjust the satellite trajectory.

[0065] According to a fourth specific embodiment of the present invention, the present invention provides an altitude adjustment method applicable to a sun-synchronous satellite, using the altitude adjustment system applicable to a sun-synchronous satellite of the third specific embodiment, comprising the following steps: Calculating the attenuation rate of the sun-synchronous satellite according to the attenuation rate calculation method applicable to the sun-synchronous satellite of the second specific implementation manner; Step S6: determining the semi-major axis increment and time interval required to adjust the satellite trajectory according to the attenuation rate; adjusting the satellite orbit according to the semi-major axis increment and time interval required to adjust the satellite trajectory.

[0066] Adjust the satellite trajectory to the east of the nominal trajectory The semi-major axis increment required for adjustment is 2△a, and the adjustment time interval is ; Among them, △λ represents the maximum value of the satellite sub-satellite point trajectory drift, that is, the geographic longitude range of the satellite actual sub-satellite point trajectory relative to the nominal trajectory is ; △a represents the semi-major axis increment required to control the satellite sub-satellite point trajectory to the nominal trajectory when it drifts to the eastern boundary; Represents the decay rate of the semi-major axis of the satellite orbit.

[0067] During the long-term orbital operation of the satellite, due to the influence of atmospheric drag, the non-spherical gravity of the earth, and the gravitational perturbations of the sun and the moon, the semi-major axis will continue to decay and cause the ground track to drift eastward and deviate from the nominal orbit. Therefore, in order to maintain the regressive characteristics of the satellite orbit, the semi-major axis needs to be adjusted periodically to maintain the performance indicators of the actual operating orbit. That is to say, when the satellite's sub-satellite point trajectory remains within a certain range near the nominal trajectory, it meets the requirements. If it exceeds the range, the orbit must be maintained.

[0068] The effect of atmospheric drag on the orbit is mainly to attenuate the semi-major axis a, and its attenuation rate is: ; in, is the decay rate, C D is the drag coefficient, A is the satellite's windward area, m is the satellite's mass, and n is the satellite's average angular velocity. is the atmospheric density at the corresponding height.

[0069] Assume that the actual trajectory remains within the nominal trajectory. If the range is within , then the variation of the semi-major axis should be: ; in The nominal semi-major axis of the satellite, i.e., it is controlled to the east of the nominal trajectory each time The adjustment of the semi-major axis is 2△a, and the adjustment time interval is (like Figure 4 as shown).

[0070] Figure 4 The horizontal axis represents the geographical longitude of the subsatellite point, and the vertical axis is the semi-major axis of the satellite. is the nominal semi-major axis of the satellite, △a represents the semi-major axis increment required to control the nominal trajectory when the satellite sub-satellite point trajectory drifts to the eastern boundary; λ0 is the nominal sub-satellite point longitude, △λ represents the maximum value of the satellite sub-satellite point trajectory drift, that is, the geographic longitude range of the satellite actual sub-satellite point trajectory relative to the nominal trajectory is .

[0071] During the satellite's flight in orbit, it will be affected by various perturbations, causing the satellite's semi-major axis to gradually decrease. When the satellite's semi-major axis is greater than the nominal semi-major axis, the sub-satellite point trajectory drifts westward; when the satellite's semi-major axis is greater than the nominal semi-major axis, the sub-satellite point trajectory drifts eastward. Therefore, the sub-satellite point trajectory is maintained at a constant level by adjusting the semi-major axis. period.

[0072] Figure 4 It means that when the longitude of the subsatellite point is And the semi-major axis is When the satellite's semi-major axis is raised by 2△a, and the satellite's semi-major axis is greater than the nominal semi-major axis, the sub-satellite point trajectory drifts westward; when it drifts westward to The semi-major axis is ; When the mean semi-major axis is smaller than the nominal mean semi-major axis, the subsatellite point trajectory drifts eastward; when it drifts eastward to The semi-major axis is ; Repeat the above operation to maintain the sub-satellite point trajectory.

[0073] In summary, the semi-major axis increment, holding period, control frequency, etc. required to maintain the satellite trajectory can be calculated based on the satellite's attenuation rate.

[0074] According to a fifth specific embodiment of the present invention, the present invention provides an electronic device, such as Figure 5 As shown, Figure 5 It is a block diagram of an electronic device according to an exemplary embodiment.

[0075] Refer to the following Figure 5 The electronic device 500 according to this embodiment of the present application is described. Figure 5 The electronic device 500 shown is merely an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0076] like Figure 5 As shown, the electronic device 500 is in the form of a general computing device. The components of the electronic device 500 may include, but are not limited to: at least one processing unit 510, at least one storage unit 520, a bus 530 connecting different system components (including the storage unit 520 and the processing unit 510), a display unit 540, etc.

[0077] The storage unit stores program codes, which can be executed by the processing unit 510, so that the processing unit 510 performs the steps described in this specification according to various exemplary embodiments of the present application. For example, the processing unit 510 can perform the steps shown in the second specific embodiment.

[0078] The storage unit 520 may include a readable medium in the form of a volatile storage unit, such as a random access memory unit (RAM) 5201 and / or a cache memory unit 5202 , and may further include a read-only memory unit (ROM) 5203 .

[0079] The storage unit 520 may also include a program / utility 5204 having a set (at least one) of program modules 5205, such program modules 5205 including but not limited to: an operating system, one or more application programs, other program modules and program data, each of which or some combination may include the implementation of a network environment.

[0080] Bus 530 may represent one or more of several types of bus structures, including a memory unit bus or memory unit controller, a peripheral bus, an accelerated graphics port, a processing unit, or a local bus using any of a variety of bus architectures.

[0081] The electronic device 500 may also communicate with one or more external devices 500' (e.g., keyboards, pointing devices, Bluetooth devices, etc.) so that a user can communicate with the device that interacts with the electronic device 500, and / or the electronic device 500 can communicate with any device that communicates with one or more other computing devices (e.g., routers, modems, etc.). Such communication may be performed through an input / output (I / O) interface 550. In addition, the electronic device 500 may also communicate with one or more networks (e.g., local area networks (LANs), wide area networks (WANs), and / or public networks, such as the Internet) through a network adapter 460. The network adapter 560 may communicate with other modules of the electronic device 500 through a bus 530. It should be understood that, although not shown in the figure, other hardware and / or software modules may be used in conjunction with the electronic device 500, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems, etc.

[0082] Through the description of the above implementations, those skilled in the art can easily understand that the example implementations described here can be implemented by software, or by combining software with necessary hardware.

[0083] Therefore, according to a sixth specific embodiment of the present invention, the present invention provides a computer readable medium. Figure 6As shown, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, and includes a number of instructions to enable a computing device (which can be a personal computer, a server, or a network device, etc.) to execute the above method according to the embodiment of the present invention.

[0084] The software product may be any combination of one or more readable media. The readable medium may be a readable signal medium or a readable storage medium. The readable storage medium may be, for example, but not limited to, a system, device or component of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination thereof. More specific examples (non-exhaustive list) of readable storage media include: an electrical connection with one or more wires, a portable disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof.

[0085] The computer readable storage medium may include a data signal propagated in a baseband or as part of a carrier wave, wherein a readable program code is carried. This propagated data signal may take a variety of forms, including but not limited to an electromagnetic signal, an optical signal, or any suitable combination of the above. The readable storage medium may also be any readable medium other than a readable storage medium, which may send, propagate, or transmit a program for use by an instruction execution system, an apparatus, or a device or used in combination with it. The program code contained on the readable storage medium may be transmitted with any appropriate medium, including but not limited to wireless, wired, optical cable, RF, etc., or any suitable combination of the above.

[0086] Program code for performing the operations of the present invention may be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java, C++, etc., and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, as a separate software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server. In the case of a remote computing device, the remote computing device may be connected to the user computing device through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0087] The computer-readable medium carries one or more programs. When the one or more programs are executed by a device, the computer-readable medium implements the functions of the second specific implementation.

[0088] Those skilled in the art will appreciate that the above modules can be distributed in the device according to the description of the embodiment, or can be changed accordingly and only used in one or more devices different from the embodiment. The modules of the above embodiments can be combined into one module, or further divided into multiple sub-modules.

[0089] Through the description of the above embodiments, it is easy for those skilled in the art to understand that the exemplary embodiments described here can be implemented by software, or by software combined with necessary hardware. Therefore, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which can be a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the method according to the embodiment of the present invention.

[0090] The exemplary embodiments of the present invention are specifically shown and described above. It should be understood that the present invention is not limited to the detailed structure, configuration or implementation method described herein; on the contrary, the present invention is intended to cover various modifications and equivalent configurations included in the spirit and scope of the appended claims.

Claims

1. A method for calculating the attenuation rate of a sun-synchronous satellite, characterized in that: The following steps are involved: S1: Get the current orbital altitude of the sun-synchronous satellite; S2: Determine a data collection period according to the current orbit altitude; S3: starting from the current moment, collecting orbital height data within the data collection period; S4: Fitting the collected orbital height data into a linearly decreasing straight line and obtaining a straight line formula; S5: Calculate the attenuation rate of the sun-synchronous satellite based on the straight-line formula.

2. The attenuation rate calculation method applicable to a sun-synchronous satellite according to claim 1, characterized in that: In step S3, collecting the orbital height data within the data collection duration starting from the current moment includes: collecting the orbital height data within the data collection duration starting from the current moment at specified time intervals; the specified time is not less than 1 minute and not more than 1 hour.

3. The attenuation rate calculation method applicable to a sun-synchronous satellite according to claim 1, characterized in that: In step S4, fitting the collected orbital height data into a linearly decreasing straight line includes: adopting a linear regression fitting method.

4. The attenuation rate calculation method applicable to a sun-synchronous satellite according to claim 1, characterized in that: In step S5, the attenuation rate of the sun-synchronous satellite is calculated according to the straight line formula, including: The straight line formula includes a slope, and the attenuation rate of the sun-synchronous satellite is obtained according to the slope; The method of obtaining the attenuation rate of a sun-synchronous satellite according to the slope includes: obtaining the attenuation of the semi-major axis of the satellite orbit per minute according to the slope, and calculating the attenuation of the semi-major axis of the satellite orbit per day according to the attenuation of the semi-major axis of the satellite orbit per minute, that is, the attenuation rate of the sun-synchronous satellite.

5. A decay rate calculation system suitable for a sun-synchronous satellite, characterized in that: include: The current orbit altitude acquisition module is used to acquire the current orbit altitude of the sun-synchronous satellite; A time period determination module, communicatively connected to the current orbit height acquisition module, for determining a data collection time period according to the current orbit height; A collection module, communicatively connected to the time period determination module and the current orbit height acquisition module, for collecting orbit height data within the data collection time period starting from the current moment; A fitting module, communicatively connected to the acquisition module, for fitting the acquired orbit height data into a linearly decreasing straight line and obtaining a straight line formula; The attenuation rate calculation module is communicatively connected with the fitting module and is used to calculate the attenuation rate of the sun-synchronous satellite according to the straight line formula.

6. A method for adjusting the altitude of a sun-synchronous satellite, characterized in that: The following steps are involved: Calculating the attenuation rate of a sun-synchronous satellite according to the attenuation rate calculation method applicable to a sun-synchronous satellite according to any one of claims 1 to 4; The semi-major axis increment and time interval required for adjusting the satellite trajectory are determined according to the attenuation rate; and the orbit of the satellite is adjusted according to the semi-major axis increment and time interval required for adjusting the satellite trajectory.

7. The altitude adjustment method for a sun-synchronous satellite according to claim 6, characterized in that: Adjust the satellite trajectory to the east of the nominal trajectory The semi-major axis increment required for adjustment is 2△a, and the adjustment time interval is ; Among them, △λ represents the maximum value of the satellite sub-satellite point trajectory drift, that is, the geographic longitude range of the satellite actual sub-satellite point trajectory relative to the nominal trajectory is ; △a represents the semi-major axis increment required to control the satellite sub-satellite point trajectory to the nominal trajectory when it drifts to the eastern boundary; Represents the decay rate of the semi-major axis of the satellite orbit.

8. An altitude adjustment system for a sun-synchronous satellite, characterized in that: include: The attenuation rate calculation system and altitude adjustment module applicable to a sun-synchronous satellite as described in claim 5; The altitude adjustment module is used to determine the semi-major axis increment and time interval required to adjust the satellite trajectory according to the attenuation rate of the sun-synchronous satellite calculated by the attenuation rate calculation system applicable to the sun-synchronous satellite; and adjust the orbit of the satellite according to the semi-major axis increment and time interval required to adjust the satellite trajectory.

9. An electronic device, characterized in that: include: one or more processors; A storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the attenuation rate calculation method applicable to a sun-synchronous satellite as described in any one of claims 1 to 4.

10. A computer readable medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the attenuation rate calculation method applicable to a sun-synchronous satellite as described in claims 1-4 is implemented.

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