Method and device for calculating orbit height of medium-inclination low earth orbit satellite, terminal and medium

Abstract

This invention discloses a method, apparatus, terminal, and storage medium for calculating the orbital altitude of a medium-inclination low-Earth orbit (LEO) satellite. The method includes: determining the periodic pattern of the LEO satellite's orbital changes; based on the periodic pattern of the LEO satellite's orbital changes, obtaining the orbital altitude difference of the LEO satellite in each of n consecutive periods; where n is a positive integer and greater than or equal to 2; and determining the orbital altitude of the LEO satellite based on the orbital altitude difference in each of the n consecutive periods, so as to apply the orbital altitude of the LEO satellite to the phase difference orbital control of the LEO satellite. This scheme accurately calculates the average orbital altitude of the LEO satellite based on its orbital characteristics and attenuation, and then applies this calculation to the fine-grained phase difference orbital control of the LEO satellite.

Description

Technical Field

[0001] This invention belongs to the field of low-Earth orbit satellite technology, specifically relating to a method, device, terminal, and storage medium for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite, and more particularly to a method, device, terminal, and storage medium for calculating the average orbital altitude of a medium-inclination low-Earth orbit satellite suitable for maintaining fine orbital control by maintaining phase difference. Background Technology

[0002] Medium-inclination low-Earth orbit satellites refer to low-Earth orbit satellites with an orbital inclination between 30 and 65 degrees. These satellites have some unique characteristics and advantages, such as:

[0003] 1) Medium-inclination low-Earth orbit (LEO) satellites have relatively low orbital altitudes, typically between several hundred and over a thousand kilometers. This low orbit allows LEO satellites to better cover areas of the Earth's surface and provide more timely and comprehensive information.

[0004] 2) Medium-inclination low-Earth orbit (LEO) satellites have shorter transmission delays. Because LEO satellites are closer to Earth, their signal transmission speed is faster and the delay time is shorter, which is very important for applications that require real-time communication.

[0005] 3) Medium-inclination low-Earth orbit (LEO) satellites have a wider coverage area. Due to their lower orbital altitude, LEO satellites can cover a wider area, which is highly advantageous for applications such as meteorological observation and geographic information systems.

[0006] 4) Medium-inclination LEO satellites offer higher observation resolution. Because they are closer to Earth, medium-inclination LEO satellites can provide higher resolution images and data, which is crucial for many applications that require such high-resolution images and data.

[0007] Medium-inclination low-Earth orbit (LEO) satellites are subject to various perturbations during their orbital operation, which can cause deviations and changes in their orbits. Common perturbations include the Earth's non-spherical perturbation, the gravitational pull of the Sun and Moon, atmospheric drag, solar radiation pressure, and tidal forces. Satellite orbits are represented in two ways: instantaneous root and average root. The instantaneous root represents the orbital elements of a satellite at a specific moment, describing its position and velocity at that instant. The average root represents the average elements obtained by averaging the satellite's orbit, describing the average properties of the orbit. The difference between the average root and the instantaneous root lies in considering the influence of perturbations on the orbit. Because the average root eliminates short-period variations and only considers long-term variations, it reflects the long-term trend of orbital changes, greatly simplifying orbital perturbation analysis. Therefore, the average root is frequently used to calculate the orbital altitude of a satellite.

[0008] A satellite constellation is a system that distributes multiple satellites at specific locations in Earth's orbit. These satellites cooperate to form a constellation to provide global communication, navigation, remote sensing, and other services. To achieve a specific task, users establish different phase differences between the satellites in the constellation, and the phase difference between two satellites needs to be maintained within a certain range over a long period. Once this range is exceeded, orbit control is required. However, calculating the average orbital altitude of medium-inclination low-Earth orbit (LEO) satellites during their orbital operation is quite challenging.

[0009] Therefore, there is an urgent need to develop a method, device, terminal, and storage medium for calculating the orbital altitude of medium-inclination low-Earth orbit (LEO) satellites, which can accurately calculate the average orbital altitude of LEO satellites and then be applied to fine orbit control for maintaining the phase difference of LEO satellites.

[0010] The above content is only used to help understand the technical solution of the present invention and does not represent an admission that the above content is prior art. Summary of the Invention

[0011] The purpose of this invention is to provide a method, apparatus, terminal, and storage medium for calculating the orbital altitude of a medium-inclination low-Earth orbit (LEO) satellite, thereby solving the problem of the difficulty in calculating the average orbital altitude of a LEO satellite during orbital control. This invention achieves the goal of accurately calculating the average orbital altitude of a LEO satellite based on its orbital characteristics and attenuation, and then applying this calculation to maintain precise orbital control of the LEO satellite's phase difference.

[0012] This invention provides a method for calculating the orbital altitude of a medium-inclination low-Earth orbit (LEO) satellite, comprising: determining the periodic pattern of the orbital variation of the LEO satellite; based on the periodic pattern of the orbital variation of the LEO satellite, obtaining the orbital altitude difference of the LEO satellite in each of n consecutive periods; where n is a positive integer and n is greater than or equal to 2; determining the orbital altitude of the LEO satellite according to the orbital altitude difference of the LEO satellite in each of the n consecutive periods, so as to apply the orbital altitude of the LEO satellite to the phase difference orbit control of the LEO satellite.

[0013] In some implementations, determining the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite includes: analyzing the orbital changes of the intermediate-inclination low-Earth orbit satellite over time to obtain information showing that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend; and calculating the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite based on the fact that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend.

[0014] In some implementations, based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend, the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite is calculated, including: generating a trend map of the orbit of the medium-inclination low-Earth orbit satellite fluctuating up and down and having a periodic decreasing trend based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend based on the maximum or minimum points in the trend map of the orbit of the medium-inclination low-Earth orbit satellite fluctuating up and down and having a periodic decreasing trend, calculating n periods of the orbital change of the medium-inclination low-Earth orbit satellite to form the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite.

[0015] In some implementations, determining the orbital altitude of the medium-inclination low-Earth orbit (LEO) satellite based on the orbital altitude difference in each of n consecutive cycles includes: calculating the average value of the orbital altitude differences of the LEO satellite over the n consecutive cycles; using the average value of the orbital altitude differences of the LEO satellite over the n consecutive cycles as the altitude difference between two satellites in the constellation of the LEO satellite, thereby determining the orbital altitude of the LEO satellite and applying it to the phase difference orbit control of the LEO satellite.

[0016] In conjunction with the above method, another aspect of the present invention provides an orbital altitude calculation device for a medium-inclination low-Earth orbit (LEO) satellite, comprising: a control unit configured to determine the periodic pattern of orbital changes of the LEO satellite; an acquisition unit configured to acquire, based on the periodic pattern of orbital changes of the LEO satellite, the orbital altitude difference of the LEO satellite in each of n consecutive periods; where n is a positive integer and n is greater than or equal to 2; the control unit is further configured to determine the orbital altitude of the LEO satellite based on the orbital altitude difference of the LEO satellite in each of the n consecutive periods, so as to apply the orbital altitude of the LEO satellite to the phase difference orbital control of the LEO satellite.

[0017] In some embodiments, the control unit determines the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite by: analyzing the orbital changes of the intermediate-inclination low-Earth orbit satellite over time to obtain information showing that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend; and calculating the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite based on the information showing that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend.

[0018] In some embodiments, the control unit calculates the periodic pattern of the orbital change of the intermediate-inclination low-Earth orbit satellite based on the fact that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend. This includes: generating a trend graph of the orbital change of the intermediate-inclination low-Earth orbit satellite fluctuating up and down and having a periodic decreasing trend based on the fact that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend based on the maximum or minimum points in the trend graph of the orbital change of the intermediate-inclination low-Earth orbit satellite, so as to form the periodic pattern of the orbital change of the intermediate-inclination low-Earth orbit satellite.

[0019] In some embodiments, the control unit determines the orbital altitude of the medium-inclination low-Earth orbit satellite based on the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles. This includes: calculating the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over the n consecutive cycles; and using the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over the n consecutive cycles as the altitude difference between two satellites in the constellation of the medium-inclination low-Earth orbit satellite, thereby determining the orbital altitude of the medium-inclination low-Earth orbit satellite and applying the orbital altitude of the medium-inclination low-Earth orbit satellite to the phase difference orbit control of the medium-inclination low-Earth orbit satellite.

[0020] In conjunction with the aforementioned device, the present invention further provides a terminal, comprising: the orbital altitude calculation device for medium-inclination low-Earth orbit satellites described above.

[0021] In conjunction with the above method, the present invention further provides a storage medium comprising a stored program, wherein, when the program is executed, the device containing the storage medium executes the above-described method for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite.

[0022] Therefore, the solution of this invention first analyzes the periodic pattern of the orbital changes of medium-inclination low-Earth orbit satellites by considering that the orbits of medium-inclination low-Earth orbit satellites fluctuate up and down and have a periodic decay trend. Then, it calculates the average value of the orbital altitude difference of medium-inclination low-Earth orbit satellites within several periods as the altitude difference between the two satellites in the medium-inclination low-Earth orbit satellite constellation, so as to accurately calculate the average orbital altitude of medium-inclination low-Earth orbit satellites. Thus, by accurately calculating the average orbital altitude of medium-inclination low-Earth orbit satellites based on the characteristics and decay of their orbits, it can be applied to fine orbit control for maintaining the phase difference of medium-inclination low-Earth orbit satellites.

[0023] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention.

[0024] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0025] Figure 1 This is a flowchart illustrating an embodiment of the method for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite according to the present invention.

[0026] Figure 2 This is a flowchart illustrating an embodiment of the method of the present invention for determining the periodic pattern of orbital changes of a medium-inclination low-Earth orbit satellite.

[0027] Figure 3 This is a flowchart illustrating an embodiment of the method of the present invention for calculating the periodicity of the orbital changes of the medium-inclination low-Earth orbit satellite.

[0028] Figure 4 This is a flowchart illustrating an embodiment of the method for determining the orbital altitude of a medium-inclination low-Earth orbit satellite according to the present invention.

[0029] Figure 5 This is a schematic diagram of an embodiment of the orbital altitude calculation device for a medium-inclination low-Earth orbit satellite according to the present invention;

[0030] Figure 6 A schematic diagram showing the trend of the semi-major axis of a high-inclination satellite over 100 days;

[0031] Figure 7 This is a schematic diagram showing the trend of the semi-major axis of a medium-inclination satellite's orbit over 100 days.

[0032] Figure 8 A schematic diagram of the orbital change trend curve of the binary stars over 100 days;

[0033] Figure 9 A schematic diagram of the trend curve of the orbital altitude difference between the two stars over 100 days;

[0034] Figure 10 This is a table showing the relationship between data duration and orbital altitude difference.

[0035] Referring to the accompanying drawings, the reference numerals in the embodiments of the present invention are as follows:

[0036] 102 - Acquisition unit; 104 - Control unit. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0038] Considering the difficulty in calculating the average orbital altitude of a medium-inclination low-Earth orbit (LEO) satellite during orbital control, some solutions directly use the root mean square (RMS) value at a specific moment to calculate the satellite's orbital altitude. This single-point calculation method is simple and quick, but it is only suitable for applications requiring real-time orbital information and cannot reflect long-term orbital trends. It only provides an instantaneous RMS value, resulting in relatively low accuracy of the RMS value.

[0039] In addition, some other methods use the semi-major axis of the satellite's orbit over several hours to calculate an average orbital altitude. While this method considers the long-term trend of orbital changes, it is only suitable for satellites with no significant periodic changes in their orbits, such as sun-synchronous satellites. For medium-inclination low-Earth orbit satellites, this method cannot accurately reflect changes in the satellite's orbit.

[0040] Especially when maintaining precise orbit control of satellite phase difference, it is necessary to control the satellite at a certain fixed altitude or the altitude difference between the two satellites must meet a certain fixed value. However, the methods in the relevant schemes are obviously unreasonable and not applicable to medium-inclination low-Earth orbit satellites.

[0041] Therefore, the present invention proposes a method for calculating the orbital altitude of a medium-inclination low-Earth orbit (LEO) satellite. Specifically, it is a method for calculating the average orbital altitude suitable for fine orbit control to maintain the phase difference of LEO satellites. This method fully considers the characteristics and attenuation of the LEO satellite orbit, calculates the orbital altitude of the LEO satellite, and accurately calculates the average orbital altitude of the LEO satellite, which is then applied to fine orbit control to maintain the phase difference of the LEO satellite.

[0042] According to an embodiment of the present invention, a method for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite is provided, such as... Figure 1 The diagram shows a flowchart of an embodiment of the method of the present invention. This method for calculating the orbital altitude of a low-Earth orbit satellite with medium inclination may include steps S110 to S130.

[0043] In step S110, the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite is determined.

[0044] In some implementations, the specific process of determining the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite in step S110 is illustrated in the following exemplary description.

[0045] The following is combined Figure 2 The flowchart of an embodiment of the wavelet packet analysis method in the present invention is shown below. It further illustrates the specific process of determining the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite in step S110, including steps S210 to S220.

[0046] Step S210: Analyze the orbital changes of the medium-inclination low-Earth orbit satellite over time, and find that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic trend of decay.

[0047] Step S220: Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decay trend, the periodic law of the orbit change of the medium-inclination low-Earth orbit satellite is calculated.

[0048] Satellites are subject to various perturbations during their orbital operation, such as the Earth's non-spherical perturbation, the Sun's gravity, the Moon's gravity, atmospheric drag, and solar radiation pressure. These perturbations cause the satellite's orbit to constantly change. Figure 6 This is a schematic diagram showing the trend of the semi-major axis of a high-inclination satellite over 100 days. Figure 7 This is a schematic diagram showing the 100-day orbital semi-major axis variation trend of a medium-inclination satellite. Most low-Earth orbit (LEO) satellites are medium- to high-inclination LEO satellites. Figure 6 and Figure 7 The trend of the semi-major axis of low-Earth orbit satellites with medium and high inclination angles over 100 days was analyzed.

[0049] from Figure 6 and Figure 7 It can be seen that low-Earth orbit satellites with different inclinations have different orbital change trends due to the varying degrees of influence from various perturbations. The orbits of high-inclination low-Earth orbit satellites show a linear decay trend, while the orbits of medium-inclination low-Earth orbit satellites, which are more significantly affected by the non-spherical perturbations of the Earth, exhibit a fluctuating and periodic decay trend.

[0050] In some embodiments, the specific process of calculating the periodic pattern of the orbital change of the medium-inclination low-Earth orbit satellite in step S220, based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic trend of decay, is described in the following exemplary description.

[0051] The following is combined Figure 3The flowchart shown is a schematic diagram of an embodiment of the method of the present invention for calculating the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite. It further illustrates the specific process of calculating the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite in step S220, including steps S310 to S320.

[0052] Step S310: Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend, a trend map of the orbit of the medium-inclination low-Earth orbit satellite fluctuating up and down and having a periodic decreasing trend is generated.

[0053] Step S320: Based on the maximum or minimum points in the trend graph of the medium-inclination low-Earth orbit satellite's orbit fluctuating up and down with a periodic decay trend, calculate n periods of orbital change of the medium-inclination low-Earth orbit satellite to form the periodic law of orbital change of the medium-inclination low-Earth orbit satellite.

[0054] Specifically, in the solution of this invention, for medium-inclination low-Earth orbit satellites, the semi-major axis trend of the orbits of two medium-inclination low-Earth orbit satellites over a period of 100 days or even longer is plotted. Because medium-inclination low-Earth orbit satellites are significantly affected by the non-spherical perturbation force of the Earth, their orbits exhibit up-and-down fluctuations and a periodic trend of decay (e.g., ...). Figure 7 (As shown). The approximate period of the orbital fluctuation of a medium-inclination low-Earth orbit (LEO) satellite can be calculated from the maximum or minimum points of a trend graph showing a periodic decay in the orbit. For example, in a trend graph showing a periodic decay in the orbit of a medium-inclination LEO satellite, the time interval corresponding to the two maximum or minimum points on the horizontal semi-major axis is calculated by subtracting the two time intervals; this is the approximate period.

[0055] In step S120, based on the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite, the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive periods is obtained; n is a positive integer and n is greater than or equal to 2.

[0056] In step S130, the orbital altitude of the medium-inclination low-Earth orbit satellite is determined based on the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles, so as to apply the orbital altitude of the medium-inclination low-Earth orbit satellite to the phase difference orbit control of the medium-inclination low-Earth orbit satellite.

[0057] Because the orbital decay patterns differ among different types of satellites, the methods for calculating orbital altitude also vary. Methods that directly use the square root of the satellite's orbital altitude at a specific moment or calculate an average orbital altitude using the horizontal semi-major axis of the satellite's orbit over several hours are unsuitable for medium-inclination low-Earth orbit satellites. Especially in fine-grained orbital control for maintaining satellite phase difference, the altitude difference between the two satellites determines the maintenance period of the phase difference; therefore, accurate calculation of the altitude difference between the two satellites is crucial.

[0058] Therefore, the present invention proposes an average orbital altitude calculation scheme suitable for fine orbital control of phase difference of medium-inclination low-Earth orbit satellites. This scheme fully considers the characteristics and attenuation of medium-inclination low-Earth orbit satellite orbits, calculates the orbital altitude of medium-inclination low-Earth orbit satellites, and accurately calculates the average orbital altitude of medium-inclination low-Earth orbit satellites, which can then be applied to fine orbital control for maintaining phase difference of medium-inclination low-Earth orbit satellites.

[0059] In some implementations, the specific process of determining the orbital altitude of the medium-inclination low-Earth orbit satellite in step S130 based on the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles is described in the following exemplary description.

[0060] The following is combined Figure 4 The schematic diagram shown is a flowchart of an embodiment of the method of the present invention for determining the orbital altitude of the medium-inclination low-Earth orbit satellite. It further illustrates the specific process of determining the orbital altitude of the medium-inclination low-Earth orbit satellite in step S130, including steps S410 to S420.

[0061] Step S410: For the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles, calculate the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite in the n consecutive cycles.

[0062] Step S420: The average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over n consecutive periods is used as the altitude difference between the two satellites in the constellation of the medium-inclination low-Earth orbit satellite, thereby determining the orbital altitude of the medium-inclination low-Earth orbit satellite and applying the orbital altitude of the medium-inclination low-Earth orbit satellite to the phase difference orbit control of the medium-inclination low-Earth orbit satellite.

[0063] In the present invention, by fully considering the characteristics and attenuation of the orbits of medium-inclination low-Earth orbit (LEO) satellites, it is determined that the orbits of LEO satellites fluctuate vertically and exhibit a periodic attenuation trend. In other words, the orbits of LEO satellites fluctuate vertically and exhibit a periodic attenuation trend. Based on these characteristics and attenuation, the specific calculation scheme for calculating the orbital altitude of LEO satellites includes: first, analyzing the periodic pattern of orbital changes; then, calculating the average value of the orbital altitude difference within several periods as the altitude difference between the two satellites in the LEO satellite constellation. This allows for the accurate calculation of the average orbital altitude of the LEO satellites, which can then be applied to fine-grained orbit control for maintaining the phase difference of LEO satellites.

[0064] Specifically, in the solution of the present invention, according to as follows Figure 7 After calculating the approximate period of the orbital fluctuation of a medium-inclination low-Earth orbit (MEO) satellite by analyzing the maximum or minimum points of the trend graph showing the fluctuating orbit with a periodic decay, the orbital altitude difference of the MEO satellite within 1, 2, ..., n (n≥2) periods is calculated for the calculated approximate period of the orbital fluctuation. The average value is then taken as the altitude difference between two satellites in the MEO satellite constellation, and subsequent analysis is performed (such as for fine orbit control to maintain the phase difference of MEO satellites).

[0065] Figure 8 This is a schematic diagram of the orbital change trend curve of the binary stars over 100 days. Figure 9 This is a schematic diagram of the trend curve of the orbital altitude difference between the two stars over 100 days. Figure 10 This is a table showing the relationship between data duration and orbital altitude difference. The following section combines... Figure 8 , Figure 9 and Figure 10 The examples shown illustrate detailed operational instances of the solutions of the present invention.

[0066] Taking two medium-inclination low-Earth orbit satellites, A and B, at different orbital altitudes as an example, the orbital changes and trends of the orbital altitude difference over a set period of 100 days are as follows: Figure 8 and Figure 9 As shown. By fitting the 100-day orbital semi-major axis variation of the binary satellites, the orbital variation period can be analyzed to be approximately 35 days. Since the orbits of medium-inclination low-Earth orbit satellites exhibit periodic fluctuations, plotting curves of the semi-major axis for at least three periods is sufficient to fit the 100-day orbital semi-major axis variation of the binary satellites. Specifically, when calculating the period for the 100-day orbital semi-major axis variation, the time interval is calculated by subtracting the two times corresponding to the two maximum or two minimum points of the semi-major axis; this difference represents the period.

[0067] The following analysis examines the orbital altitude differences of medium-inclination low-Earth orbit (LEO) satellites calculated using LEO satellite orbital data of different durations. Figure 10 As shown in the table. In, as Figure 10 The table showing the relationship between data duration and orbital altitude difference indicates that when the data duration for a medium-inclination low-Earth orbit (LEO) satellite is 0.5 days, the altitude difference is 55.5m; when the data duration is 5 days, the altitude difference is 44.3m; when the data duration is 10 days, the altitude difference is 33.8m; when the data duration is 15 days, the altitude difference is 26.2m; and when the data duration is 20 days, the altitude difference is... The altitude difference for medium-inclination low-Earth orbit (LEO) satellites is 24.0m; when the data duration is 25 days, the altitude difference is 26.2m; when the data duration is 30 days, the altitude difference is 30.3m; when the data duration is 35 days, the altitude difference is 33.8m; when the data duration is 40 days, the altitude difference is 35.2m; when the data duration is 45 days, the altitude difference is 34.4m. When the data duration is 50 days, the altitude difference of the medium-inclination low-Earth orbit satellite orbit is 32.4m; when the data duration is 55 days, the altitude difference is 30.7m; when the data duration is 60 days, the altitude difference is 30.8m; when the data duration is 65 days, the altitude difference is 32.4m; when the data duration is 70 days, the altitude difference is 34.2m; when the data duration is 75 days, the altitude difference is... The altitude difference of the satellite orbits is 35.0m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 80 days, the altitude difference is 34.3m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 85 days, the altitude difference is 33.1m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 90 days, the altitude difference is 32.2m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 95 days, the altitude difference is 32.3m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 100 days, the altitude difference is 33.3m. Figure 10The table showing the relationship between data duration and orbital height difference reveals that the orbital height difference calculated over n consecutive orbital cycles is more accurate, while the height difference calculated without an orbital cycle is incorrect. For example, if the orbital cycle is 35 days, the orbital height difference calculated from data over 35 days and 70 days would be approximately 34 meters. If data from non-orbital cycles is used arbitrarily, the resulting orbital height difference will differ significantly from the actual value. This is especially problematic during orbit control, as the magnitude of the orbital height difference determines the maintenance period of the phase difference; therefore, accurate calculation of the orbital height difference is essential.

[0068] Obviously, in the scheme of this invention, based on the orbital variation period of medium-inclination low-Earth orbit (LEO) satellites, the altitude difference between the orbits of two satellites in a LEO satellite constellation is approximately 34m. For example, if the orbital period is 35 days, then the average altitude difference calculated from data over 35 days and 70 days is 34m. However, if the method used in related schemes to calculate an average orbital altitude using the horizontal semi-major axis of the satellite's orbit over several hours is used, the calculated altitude difference between the two satellites is approximately 55.5m, which does not match the actual altitude difference of approximately 34m. This affects the accuracy of calculating the average orbital altitude of LEO satellites, and consequently affects the reliability and safety of maintaining fine orbital control for the phase difference of LEO satellites. The solution of this invention, by fully considering the characteristics and attenuation of medium-inclination low-Earth orbit (LEO) satellite orbits, first analyzes the periodic pattern of LEO satellite orbit changes, and then calculates the average value of the LEO satellite orbit altitude difference over several periods as the altitude difference between the two satellites in the LEO satellite constellation. Thus, the average orbital altitude of LEO satellites can be accurately calculated, and this can be applied to the fine orbit control of LEO satellite phase difference maintenance, which is beneficial to improving the reliability and safety of fine orbit control of LEO satellite phase difference maintenance.

[0069] The technical solution of this embodiment first analyzes the periodic pattern of the orbital changes of medium-inclination low-Earth orbit (MEO) satellites by considering that their orbits fluctuate up and down and exhibit a periodic decay trend. Then, it calculates the average altitude difference of the MEO satellite orbits over several periods as the altitude difference between the two satellites in the MEO satellite constellation, thereby accurately calculating the average orbital altitude of the MEO satellites. Thus, by accurately calculating the average orbital altitude of the MEO satellites based on their orbital characteristics and decay, this method can be applied to fine orbit control for maintaining the phase difference of MEO satellites.

[0070] According to embodiments of the present invention, an apparatus for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite is also provided, corresponding to a method for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite. See also Figure 5 The diagram shows a structural schematic of an embodiment of the device of the present invention. This device for calculating the orbital altitude of a low-Earth orbit satellite with a medium inclination may include: an acquisition unit 102 and a control unit 104.

[0071] The control unit 104 is configured to determine the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite. The specific functions and processing of the control unit 104 are described in step S110.

[0072] In some embodiments, the control unit 104 determines the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite, including:

[0073] The control unit 104 is further configured to analyze the orbital changes of the medium-inclination low-Earth orbit satellite over time, and to determine that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and exhibits a periodic trend of decay. The specific functions and processing of this control unit 104 are further described in step S210.

[0074] The control unit 104 is further configured to calculate the periodic pattern of the orbital changes of the intermediate-inclination low-Earth orbit satellite, based on the fact that the orbit of the satellite fluctuates up and down and has a periodic decreasing trend. The specific functions and processing of this control unit 104 are further described in step S220.

[0075] Satellites are subject to various perturbations during their orbital operation, such as the Earth's non-spherical perturbation, the Sun's gravity, the Moon's gravity, atmospheric drag, and solar radiation pressure. These perturbations cause the satellite's orbit to constantly change. Figure 6 This is a schematic diagram showing the trend of the semi-major axis of a high-inclination satellite over 100 days. Figure 7 This is a schematic diagram showing the 100-day orbital semi-major axis variation trend of a medium-inclination satellite. Most low-Earth orbit (LEO) satellites are medium- to high-inclination LEO satellites. Figure 6 and Figure 7 The trend of the semi-major axis of low-Earth orbit satellites with medium and high inclination angles over 100 days was analyzed.

[0076] from Figure 6 and Figure 7 It can be seen that low-Earth orbit satellites with different inclinations have different orbital change trends due to the varying degrees of influence from various perturbations. The orbits of high-inclination low-Earth orbit satellites show a linear decay trend, while the orbits of medium-inclination low-Earth orbit satellites, which are more significantly affected by the non-spherical perturbations of the Earth, exhibit a fluctuating and periodic decay trend.

[0077] In some embodiments, the control unit 104, based on the fact that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend, calculates the periodic law of the orbital change of the intermediate-inclination low-Earth orbit satellite, including:

[0078] The control unit 104 is further configured to generate a trend graph showing that the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates vertically and exhibits a periodic decreasing trend, based on the situation where the orbit of the intermediate-inclination low-Earth orbit satellite fluctuates vertically and exhibits a periodic decreasing trend. The specific functions and processing of this control unit 104 are further described in step S310.

[0079] The control unit 104 is further configured to calculate n periods of orbital variation of the medium-inclination low-Earth orbit satellite based on the maximum or minimum points in the trend graph of the satellite's orbit fluctuating up and down with a periodic decay trend, thereby forming a periodic pattern of orbital variation of the medium-inclination low-Earth orbit satellite. The specific functions and processing of this control unit 104 are further described in step S320.

[0080] Specifically, in the solution of this invention, for medium-inclination low-Earth orbit satellites, the semi-major axis trend of the orbits of two medium-inclination low-Earth orbit satellites over a period of 100 days or even longer is plotted. Because medium-inclination low-Earth orbit satellites are significantly affected by the non-spherical perturbation force of the Earth, their orbits exhibit up-and-down fluctuations and a periodic trend of decay (e.g., ...). Figure 7 (As shown). The approximate period of the orbital fluctuation of a medium-inclination low-Earth orbit (LEO) satellite can be calculated from the maximum or minimum points of a trend graph showing a periodic decay in the orbit. For example, in a trend graph showing a periodic decay in the orbit of a medium-inclination LEO satellite, the time interval corresponding to the two maximum or minimum points on the horizontal semi-major axis is calculated by subtracting the two time intervals; this is the approximate period.

[0081] The acquisition unit 102 is configured to acquire the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of n consecutive periods, based on the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite; n is a positive integer and n is greater than or equal to 2. For the specific functions and processing of this acquisition unit 102, please refer to step S120.

[0082] The control unit 104 is further configured to determine the orbital altitude of the medium-inclination low-Earth orbit satellite based on the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of n consecutive cycles, so as to apply the orbital altitude of the medium-inclination low-Earth orbit satellite to the phase difference orbit control of the medium-inclination low-Earth orbit satellite. The specific functions and processing of this control unit 104 are further described in step S130.

[0083] Because the orbital decay patterns differ among different types of satellites, the methods for calculating orbital altitude also vary. Methods that directly use the square root of the satellite's orbital altitude at a specific moment or calculate an average orbital altitude using the horizontal semi-major axis of the satellite's orbit over several hours are unsuitable for medium-inclination low-Earth orbit satellites. Especially in fine-grained orbital control for maintaining satellite phase difference, the altitude difference between the two satellites determines the maintenance period of the phase difference; therefore, accurate calculation of the altitude difference between the two satellites is crucial.

[0084] Therefore, the present invention proposes an average orbital altitude calculation scheme suitable for fine orbital control of phase difference of medium-inclination low-Earth orbit satellites. This scheme fully considers the characteristics and attenuation of medium-inclination low-Earth orbit satellite orbits, calculates the orbital altitude of medium-inclination low-Earth orbit satellites, and accurately calculates the average orbital altitude of medium-inclination low-Earth orbit satellites, which can then be applied to fine orbital control for maintaining phase difference of medium-inclination low-Earth orbit satellites.

[0085] In some embodiments, the control unit 104 determines the orbital altitude of the intermediate-inclination low-Earth orbit satellite based on the orbital altitude difference of the satellite in each of n consecutive cycles, including:

[0086] The control unit 104 is further configured to calculate the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over n consecutive periods, for each period in the n consecutive periods. The specific functions and processing of this control unit 104 are further described in step S410.

[0087] The control unit 104 is further configured to use the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over n consecutive periods as the altitude difference between two satellites in the constellation of the medium-inclination low-Earth orbit satellites, thereby determining the orbital altitude of the medium-inclination low-Earth orbit satellites and applying the orbital altitude of the medium-inclination low-Earth orbit satellites to the phase difference orbit control of the medium-inclination low-Earth orbit satellites. The specific functions and processing of this control unit 104 are further described in step S420.

[0088] In the present invention, by fully considering the characteristics and attenuation of the orbits of medium-inclination low-Earth orbit (LEO) satellites, it is determined that the orbits of LEO satellites fluctuate vertically and exhibit a periodic attenuation trend. In other words, the orbits of LEO satellites fluctuate vertically and exhibit a periodic attenuation trend. Based on these characteristics and attenuation, the specific calculation scheme for calculating the orbital altitude of LEO satellites includes: first, analyzing the periodic pattern of orbital changes; then, calculating the average value of the orbital altitude difference within several periods as the altitude difference between the two satellites in the LEO satellite constellation. This allows for the accurate calculation of the average orbital altitude of the LEO satellites, which can then be applied to fine-grained orbit control for maintaining the phase difference of LEO satellites.

[0089] Specifically, in the solution of the present invention, according to as follows Figure 7 After calculating the approximate period of the orbital fluctuation of a medium-inclination low-Earth orbit (MEO) satellite by analyzing the maximum or minimum points of the trend graph showing the fluctuating orbit with a periodic decay, the orbital altitude difference of the MEO satellite within 1, 2, ..., n (n≥2) periods is calculated for the calculated approximate period of the orbital fluctuation. The average value is then taken as the altitude difference between two satellites in the MEO satellite constellation, and subsequent analysis is performed (such as for fine orbit control to maintain the phase difference of MEO satellites).

[0090] Figure 8 This is a schematic diagram of the orbital change trend curve of the binary stars over 100 days. Figure 9 This is a schematic diagram of the trend curve of the orbital altitude difference between the two stars over 100 days. Figure 10 This is a table showing the relationship between data duration and orbital altitude difference. The following section combines... Figure 8 , Figure 9 and Figure 10 The examples shown illustrate detailed operational instances of the solutions of the present invention.

[0091] Taking two medium-inclination low-Earth orbit satellites, A and B, at different orbital altitudes as an example, the orbital changes and trends of the orbital altitude difference over a set period of 100 days are as follows: Figure 8 and Figure 9 As shown. By fitting the 100-day orbital semi-major axis variation of the binary satellites, the orbital variation period can be analyzed to be approximately 35 days. Since the orbits of medium-inclination low-Earth orbit satellites exhibit periodic fluctuations, plotting curves of the semi-major axis for at least three periods is sufficient to fit the 100-day orbital semi-major axis variation of the binary satellites. Specifically, when calculating the period for the 100-day orbital semi-major axis variation, the time interval is calculated by subtracting the two times corresponding to the two maximum or two minimum points of the semi-major axis; this difference represents the period.

[0092] The following analysis examines the orbital altitude differences of medium-inclination low-Earth orbit (LEO) satellites calculated using LEO satellite orbital data of different durations. Figure 10 As shown in the table. In, as Figure 10 The table showing the relationship between data duration and orbital altitude difference indicates that when the data duration for a medium-inclination low-Earth orbit (LEO) satellite is 0.5 days, the altitude difference is 55.5m; when the data duration is 5 days, the altitude difference is 44.3m; when the data duration is 10 days, the altitude difference is 33.8m; when the data duration is 15 days, the altitude difference is 26.2m; and when the data duration is 20 days, the altitude difference is... The altitude difference for medium-inclination low-Earth orbit (LEO) satellites is 24.0m; when the data duration is 25 days, the altitude difference is 26.2m; when the data duration is 30 days, the altitude difference is 30.3m; when the data duration is 35 days, the altitude difference is 33.8m; when the data duration is 40 days, the altitude difference is 35.2m; when the data duration is 45 days, the altitude difference is 34.4m. When the data duration is 50 days, the altitude difference of the medium-inclination low-Earth orbit satellite orbit is 32.4m; when the data duration is 55 days, the altitude difference is 30.7m; when the data duration is 60 days, the altitude difference is 30.8m; when the data duration is 65 days, the altitude difference is 32.4m; when the data duration is 70 days, the altitude difference is 34.2m; when the data duration is 75 days, the altitude difference is... The altitude difference of the satellite orbits is 35.0m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 80 days, the altitude difference is 34.3m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 85 days, the altitude difference is 33.1m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 90 days, the altitude difference is 32.2m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 95 days, the altitude difference is 32.3m; when the data duration of the medium-inclination low-Earth orbit satellite orbits is 100 days, the altitude difference is 33.3m. Figure 10The table showing the relationship between data duration and orbital height difference reveals that the orbital height difference calculated over n consecutive orbital cycles is more accurate, while the height difference calculated without an orbital cycle is incorrect. For example, if the orbital cycle is 35 days, the orbital height difference calculated from data over 35 days and 70 days would be approximately 34 meters. If data from non-orbital cycles is used arbitrarily, the resulting orbital height difference will differ significantly from the actual value. This is especially problematic during orbit control, as the magnitude of the orbital height difference determines the maintenance period of the phase difference; therefore, accurate calculation of the orbital height difference is essential.

[0093] Obviously, in the scheme of this invention, based on the orbital variation period of medium-inclination low-Earth orbit (LEO) satellites, the altitude difference between the orbits of two satellites in a LEO satellite constellation is approximately 34m. For example, if the orbital period is 35 days, then the average altitude difference calculated from data over 35 days and 70 days is 34m. However, if the method used in related schemes to calculate an average orbital altitude using the horizontal semi-major axis of the satellite's orbit over several hours is used, the calculated altitude difference between the two satellites is approximately 55.5m, which does not match the actual altitude difference of approximately 34m. This affects the accuracy of calculating the average orbital altitude of LEO satellites, and consequently affects the reliability and safety of maintaining fine orbital control for the phase difference of LEO satellites. The solution of this invention, by fully considering the characteristics and attenuation of medium-inclination low-Earth orbit (LEO) satellite orbits, first analyzes the periodic pattern of LEO satellite orbit changes, and then calculates the average value of the LEO satellite orbit altitude difference over several periods as the altitude difference between the two satellites in the LEO satellite constellation. Thus, the average orbital altitude of LEO satellites can be accurately calculated, and this can be applied to the fine orbit control of LEO satellite phase difference maintenance, which is beneficial to improving the reliability and safety of fine orbit control of LEO satellite phase difference maintenance.

[0094] Since the processing and functions implemented by the device in this embodiment are basically the same as the embodiments, principles and examples of the aforementioned methods, any details not covered in the description of this embodiment can be found in the relevant descriptions in the aforementioned embodiments, and will not be repeated here.

[0095] According to an embodiment of the present invention, a terminal corresponding to an orbital altitude calculation device for a medium-inclination low-Earth orbit satellite is also provided. This terminal may include: the orbital altitude calculation device for a medium-inclination low-Earth orbit satellite described above.

[0096] Since the processing and functions implemented by the terminal in this embodiment are basically the same as the embodiments, principles and examples of the aforementioned device, any details not covered in this embodiment can be found in the relevant descriptions in the aforementioned embodiments, and will not be repeated here.

[0097] According to an embodiment of the present invention, a storage medium corresponding to the orbital altitude calculation method for a medium-inclination low-Earth orbit satellite is also provided. The storage medium includes a stored program, wherein the program controls the device where the storage medium is located to execute the orbital altitude calculation method for a medium-inclination low-Earth orbit satellite described above when it is running.

[0098] Since the processing and functions implemented by the storage medium in this embodiment are basically the same as the embodiments, principles and examples of the aforementioned methods, any details not covered in this embodiment can be found in the relevant descriptions in the aforementioned embodiments, and will not be repeated here.

[0099] In summary, it is readily understood by those skilled in the art that, without conflict, the aforementioned advantageous methods can be freely combined and superimposed.

[0100] The above description is merely an embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of the claims of the present invention.

Claims

1. A method for calculating an orbital height of a medium-inclination low earth orbit satellite, characterized by, include: Determine the periodic pattern of orbital changes of the aforementioned medium-inclination low-Earth orbit satellite; Based on the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite, the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive periods is obtained; n is a positive integer and n is greater than or equal to 2; The orbital altitude of the medium-inclination low-Earth orbit satellite is determined based on the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles, so as to apply the orbital altitude of the medium-inclination low-Earth orbit satellite to the phase difference orbit control of the medium-inclination low-Earth orbit satellite. The orbital altitude of the medium-inclination low-Earth orbit satellite is determined based on the orbital altitude difference of the satellite in each of n consecutive periods, including: For the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles, calculate the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite in the n consecutive cycles; The average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over n consecutive periods is used as the altitude difference between the two satellites in the constellation of the medium-inclination low-Earth orbit satellite, thereby determining the orbital altitude of the medium-inclination low-Earth orbit satellite.

2. The method for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite according to claim 1, characterized in that, Determining the periodic pattern of orbital changes of the aforementioned medium-inclination low-Earth orbit satellite includes: Analyzing the orbital changes of the medium-inclination low-Earth orbit satellite over time reveals that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and exhibits a periodic trend of decay. Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decay trend, the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite is calculated.

3. The method for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite according to claim 2, characterized in that, Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates vertically and exhibits a periodic decay trend, the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite is calculated, including: Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend, a trend map of the orbit of the medium-inclination low-Earth orbit satellite fluctuating up and down and having a periodic decreasing trend is generated. Based on the maximum or minimum points in the trend graph of the medium-inclination low-Earth orbit satellite's orbit fluctuating up and down with a periodic decay trend, n periods of orbital change of the medium-inclination low-Earth orbit satellite are calculated to form the periodic pattern of orbital change of the medium-inclination low-Earth orbit satellite.

4. A device for calculating the orbital altitude of a medium-inclination low-Earth orbit satellite, characterized in that, include: The control unit is configured to determine the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite; The acquisition unit is configured to acquire the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of n consecutive periods, based on the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite. n is a positive integer and n is greater than or equal to 2; The control unit is further configured to determine the orbital altitude of the medium-inclination low-Earth orbit satellite based on the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles, so as to apply the orbital altitude of the medium-inclination low-Earth orbit satellite to the phase difference orbit control of the medium-inclination low-Earth orbit satellite. The orbital altitude of the medium-inclination low-Earth orbit satellite is determined based on the orbital altitude difference of the satellite in each of n consecutive periods, including: For the orbital altitude difference of the medium-inclination low-Earth orbit satellite in each of the n consecutive cycles, calculate the average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite in the n consecutive cycles; The average value of the orbital altitude difference of the medium-inclination low-Earth orbit satellite over n consecutive periods is used as the altitude difference between the two satellites in the constellation of the medium-inclination low-Earth orbit satellite, thereby determining the orbital altitude of the medium-inclination low-Earth orbit satellite.

5. The orbital altitude calculation device for a medium-inclination low-Earth orbit satellite according to claim 4, characterized in that, The control unit determines the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite, including: Analyzing the orbital changes of the medium-inclination low-Earth orbit satellite over time reveals that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and exhibits a periodic trend of decay. Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decay trend, the periodic law of the orbital change of the medium-inclination low-Earth orbit satellite is calculated.

6. The orbital altitude calculation device for a medium-inclination low-Earth orbit satellite according to claim 5, characterized in that, The control unit, based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates vertically and exhibits a periodic decay trend, calculates the periodic pattern of the orbital changes of the medium-inclination low-Earth orbit satellite, including: Based on the fact that the orbit of the medium-inclination low-Earth orbit satellite fluctuates up and down and has a periodic decreasing trend, a trend map of the orbit of the medium-inclination low-Earth orbit satellite fluctuating up and down and having a periodic decreasing trend is generated. Based on the maximum or minimum points in the trend graph of the medium-inclination low-Earth orbit satellite's orbit fluctuating up and down with a periodic decay trend, n periods of orbital change of the medium-inclination low-Earth orbit satellite are calculated to form the periodic pattern of orbital change of the medium-inclination low-Earth orbit satellite.

7. A terminal, characterized in that, include: The orbital altitude calculation device for a medium-inclination low-Earth orbit satellite as described in any one of claims 4 to 6.

8. A storage medium, characterized in that, The storage medium includes a stored program, wherein, when the program is executed, the device containing the storage medium is controlled to perform the orbital altitude calculation method for a medium-inclination low-Earth orbit satellite as described in any one of claims 1 to 3.

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