Method, device and electronic equipment for determining inter-satellite distance of satellites

Abstract

The present invention provides a method, device and electronic device for determining the inter-satellite distance of satellites, which obtains the first orbital inclination, the first latitude argument and the first ascending node right ascension of the first satellite, and obtains the second orbital inclination, the second latitude argument and the second ascending node right ascension of the second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; based on the obtained information and the pre-constructed target distance expression, the maximum distance threshold and the minimum distance threshold between the first satellite and the second satellite are determined. In this method, it is only necessary to obtain the orbital inclination, latitude argument and ascending node right ascension corresponding to the first satellite and the second satellite, and the maximum distance threshold and the minimum distance threshold corresponding to the first satellite and the second satellite can be calculated by the target distance expression, and the calculation is simpler and more efficient.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite orbit research, and in particular to a method, device and electronic equipment for determining the inter-satellite distance of satellites. Background Art

[0002] In recent years, with the rapid development of satellite manufacturing, rocket reuse, and multiple satellites in one rocket, it has become a reality to deploy large-scale constellations in space. At present, many companies have proposed low-orbit giant constellation plans, among which some companies have deployed thousands of satellites in orbit. In all aspects of the construction of giant constellation systems, constellation design is the prerequisite for ensuring the normal operation of the constellation, and it is also the key to determining the performance and application level of the constellation system. For low-orbit giant constellations, a substantial increase in the number of satellites will lead to an increase in the risk of internal collisions in the constellation, which seriously threatens space safety. Therefore, analyzing and determining the constraints for collision avoidance is one of the elements of the design of low-orbit giant constellations. However, for the calculation of the maximum value of the inter-satellite distance between two satellites in the same shell, the relevant technology lacks a simple and efficient solution. Summary of the invention

[0003] The object of the present invention is to provide a method, device and electronic equipment for determining the inter-satellite distance of satellites, so as to provide a simple and efficient solution for calculating the maximum inter-satellite distance between two satellites in the same shell.

[0004] The present invention provides a method for determining the inter-satellite distance of satellites, the method comprising: obtaining a first orbital inclination, a first latitude argument and a first ascending node right ascension of a first satellite, and obtaining a second orbital inclination, a second latitude argument and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument and the second ascending node right ascension and a pre-constructed target distance expression, determining a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite.

[0005] Furthermore, the target distance expression includes: a maximum distance expression and a minimum distance expression.

[0006] Furthermore, based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument, the second ascending node right ascension and a pre-constructed target distance expression, the step of determining the maximum distance threshold and the minimum distance threshold between the first satellite and the second satellite includes: obtaining the radius of the earth and the orbital altitudes of the first satellite and the second satellite; substituting the earth radius, the orbital altitude, the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument, and the second ascending node right ascension into the maximum distance expression to obtain the maximum distance threshold between the first satellite and the second satellite; substituting the earth radius, the orbital altitude, the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument, and the second ascending node right ascension into the minimum distance expression to obtain the minimum distance threshold between the first satellite and the second satellite.

[0007] Furthermore, the maximum distance expression is:

[0008] ;

[0009] Indicates the maximum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ;

[0010] ;

[0011] ;

[0012] ;

[0013] ;

[0014] ;

[0015] ;

[0016] The second latitude argument Argument of first latitude The difference between represents the first orbit inclination; represents the inclination of the second orbit; Indicates the right ascension of the second ascending node Right Ascension of First Ascending Node The difference between .

[0017] Furthermore, the minimum distance expression is:

[0018] ;

[0019] in, Indicates the minimum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ;

[0020] ;

[0021] ;

[0022] ;

[0023] ;

[0024] ;

[0025] ;

[0026] The second latitude argument Argument of first latitude The difference between represents the first orbit inclination; represents the inclination of the second orbit; Indicates the right ascension of the second ascending node Right Ascension of First Ascending Node The difference between .

[0027] Furthermore, the first satellite and the second satellite have the same orbital altitude.

[0028] Furthermore, the eccentricity corresponding to the first satellite and the eccentricity corresponding to the second satellite are both zero.

[0029] The present invention provides a device for determining the inter-satellite distance of satellites, the device comprising: an acquisition module, used for acquiring a first orbital inclination, a first latitude argument and a first ascending node right ascension of a first satellite, and acquiring a second orbital inclination, a second latitude argument and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; and a determination module, used for determining a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument and the second ascending node right ascension and a pre-constructed target distance expression.

[0030] An electronic device provided by the present invention includes a processor and a memory, wherein the memory stores machine executable instructions that can be executed by the processor, and the processor executes the machine executable instructions to implement any of the above-mentioned methods for determining the inter-satellite distance of satellites.

[0031] The present invention provides a machine-readable storage medium, which stores machine-executable instructions. When the machine-executable instructions are called and executed by a processor, the machine-executable instructions prompt the processor to implement any of the above-mentioned methods for determining the inter-satellite distance of satellites.

[0032] The satellite inter-satellite distance determination method, device and electronic device provided by the present invention obtain the first orbital inclination, first latitude argument and first ascending node right ascension of the first satellite, and obtain the second orbital inclination, second latitude argument and second ascending node right ascension of the second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; based on the obtained information and the pre-constructed target distance expression, the maximum distance threshold and the minimum distance threshold between the first satellite and the second satellite are determined. In this method, it is only necessary to obtain the orbital inclination, latitude argument and ascending node right ascension corresponding to the first satellite and the second satellite, and the maximum distance threshold and the minimum distance threshold corresponding to the first satellite and the second satellite can be calculated by the target distance expression, and the calculation is simpler and more efficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0034] Figure 1 A flowchart of a method for determining the inter-satellite distance of satellites provided in an embodiment of the present invention;

[0035] Figure 2 A schematic diagram of a spatial position relationship between a first satellite and a second satellite provided in an embodiment of the present invention;

[0036] Figure 3 A schematic diagram of a curve showing a change in the distance between two satellites provided by an embodiment of the present invention;

[0037] Figure 4 A device for determining the inter-satellite distance of satellites provided in an embodiment of the present invention;

[0038] Figure 5 A schematic diagram of the structure of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0039] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0040] In the related art, when it is necessary to calculate the inter-satellite distance between two satellites in the same shell, the calculation process is usually complicated and lacks a simpler and more effective solution. Based on this, the embodiments of this aspect provide a method, device and electronic equipment for determining the inter-satellite distance of satellites. This technology can be applied to the design of low-orbit giant constellations.

[0041] To facilitate understanding of this embodiment, firstly, a method for determining the inter-satellite distance of satellites disclosed in an embodiment of the present invention is introduced. Figure 1 As shown, the method comprises the following steps:

[0042] Step S102, obtaining a first orbital inclination, a first latitude argument, and a first ascending node right ascension of a first satellite, and obtaining a second orbital inclination, a second latitude argument, and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell;

[0043] The first satellite and the second satellite may be any two satellites belonging to the same satellite shell, and the first satellite and the second satellite may be adjacent or non-adjacent. The satellite shell refers to the layered deployment structure of Starlink satellites in orbit; the satellites in each satellite shell have the same orbital altitude and inclination, forming a constellation with the same orbital altitude. The orbital inclination refers to the angle between the satellite orbital plane and the earth's equatorial plane; the latitude argument refers to the amplitude of the latitude change of its ground projection point when the satellite is running in orbit; the ascending node right ascension refers to the longitude of the intersection of the satellite orbital plane and the earth's equatorial plane (i.e., the ascending node) on the equatorial plane. In actual implementation, the first orbital inclination, the first latitude argument, and the first ascending node right ascension of the first satellite, as well as the second orbital inclination, the second latitude argument, and the second ascending node right ascension of the second satellite can be obtained.

[0044] Step S104, determining a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument, the second ascending node right ascension and a pre-constructed target distance expression;

[0045] The above-mentioned maximum distance threshold can be understood as the maximum value of the distance designed between the first satellite and the second satellite when designing a low-orbit giant constellation; the above-mentioned minimum distance threshold can be understood as the minimum value of the distance designed between the first satellite and the second satellite when designing a low-orbit giant constellation; in actual implementation, the above-mentioned target distance expression can be pre-constructed. After obtaining the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument and the second ascending node right ascension, the maximum distance threshold and the minimum distance threshold between the first satellite and the second satellite can be calculated according to these parameters and the target distance expression.

[0046] The above-mentioned method for determining the inter-satellite distance of satellites obtains the first orbital inclination, the first latitude argument and the first right ascension of the ascending node of the first satellite, and obtains the second orbital inclination, the second latitude argument and the second right ascension of the ascending node of the second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; based on the first orbital inclination, the first latitude argument, the first right ascension of the ascending node, the second orbital inclination, the second latitude argument and the second right ascension of the ascending node and the pre-constructed target distance expression, the maximum distance threshold and the minimum distance threshold between the first satellite and the second satellite are determined. In this method, it is only necessary to obtain the orbital inclination, latitude argument and right ascension of the ascending node corresponding to the first satellite and the second satellite respectively, and the maximum distance threshold and the minimum distance threshold corresponding to the first satellite and the second satellite can be calculated through the target distance expression, which makes the calculation more simple and efficient.

[0047] The embodiment of the present invention also provides another method for determining the inter-satellite distance of satellites. The method is implemented on the basis of the method of the above embodiment. In this method, the target distance expression includes: a maximum distance expression and a minimum distance expression; since the first satellite and the second satellite belong to the same satellite shell, the first satellite and the second satellite have the same orbital altitude. The eccentricity corresponding to the first satellite and the eccentricity corresponding to the second satellite are both zero; wherein the eccentricity can be understood as the degree to which the satellite orbit deviates from the circular orbit. When the eccentricity is zero, the satellite orbit is circular. The method comprises the following steps:

[0048] Step 1: obtaining a first orbital inclination, a first latitude argument, and a first ascending node right ascension of a first satellite, and obtaining a second orbital inclination, a second latitude argument, and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell;

[0049] Step 3, obtaining the radius of the earth and the orbital altitudes of the first satellite and the second satellite;

[0050] Step 4, substituting the earth radius, orbital altitude, first orbital inclination, first latitude argument, first ascending node right ascension, second orbital inclination, second latitude argument, and second ascending node right ascension into the maximum distance expression to obtain the maximum distance threshold between the first satellite and the second satellite;

[0051] Step 5: Substitute the earth radius, orbital altitude, first orbital inclination, first latitude argument, first ascending node right ascension, second orbital inclination, second latitude argument and second ascending node right ascension into the minimum distance expression to obtain the minimum distance threshold between the first satellite and the second satellite.

[0052] The following is an explanation of the derivation process of the maximum distance expression and the minimum distance expression. In actual implementation, a spatial position stereo model of the first satellite and the second satellite belonging to the same satellite shell can be established in the geocentric inertial coordinate system, such as Figure 2 The schematic diagram of the spatial position relationship between a first satellite and a second satellite shown can be used to analyze the position relationship between any two first satellites and a second satellite in the same orbital shell in the geocentric inertial coordinate system based on orbital dynamics theory and related spatial geometry theory.

[0053] The above-mentioned geocentric inertial coordinate system can also be called the ECI (Earth-Centered Inertial Frame) coordinate system, which is an inertial coordinate system with the center of mass of the earth as the origin and a fixed direction. In actual implementation, the functional relationship between the spatial positions of the first satellite and the second satellite can be established in advance, and the coordinates of the first satellite and the second satellite can be determined based on the functional relationship. A three-dimensional model is used to represent the spatial positions of the first satellite and the second satellite; the X-axis of the three-dimensional model points to the vernal equinox, the Y-axis points to the positive direction of the earth's rotation axis, and the Z-axis points to the direction of the earth's North Pole. According to the coordinates of the first satellite and the second satellite, they can be drawn at the corresponding positions in the three-dimensional model, and the corresponding spatial position stereo model can be drawn according to the shape and size of each satellite to represent the satellite. The spatial position stereo model under the ECI coordinate system can convert abstract coordinate data into intuitive visual images to facilitate understanding of the position and attitude of the satellite in space.

[0054] The orbital inclination, latitude argument and ascending node right ascension of the first satellite and the second satellite are obtained respectively, such as Figure 2 As shown, Indicates the first satellite The first orbital inclination of Indicates the first satellite The first latitude argument of Indicates the first satellite The right ascension of the first ascending node; Indicates the second satellite The inclination of the second orbit; Indicates the second satellite The second latitude argument of Indicates the second satellite The right ascension of the second ascending node.

[0055] Below Figure 2 The angles in the diagram are symbolized as follows: M is the first satellite The ascending node of ascending node. are arc segments on the great circle passing through two points on the sphere. The arc segment is extended to intersect the equator at N. The arc segment is extended and intersects the equator at Q. All edges on the sphere correspond to geocentric angles, and all angles correspond to dihedral angles, among which, , ,definition , , , , is the geocentric angle corresponding to the first satellite and the second satellite, , the geocentric angle refers to the angle formed by the lines connecting the first satellite and the second satellite and the center of the earth respectively.

[0056] According to the sine and cosine theorems of spherical triangles, the relative position relationship between the first satellite and the second satellite is analyzed, and the geocentric angle between the two satellites is derived. The first orbital inclination of the first satellite , right ascension of the first ascending node , the second orbital inclination of the second satellite , right ascension of the second ascending node These are all known parameters, and the corresponding eccentricities of the first and second satellites are both 0.

[0057] Based on the theory of spherical geometry, the first orbital inclination can be calculated using the known parameters , the second orbital inclination , the first latitude argument , second latitude argument , right ascension of the first ascending node , right ascension of the second ascending node Indicates the geocentric angle According to the law of sines, on the sphere and In , we get the following relationship:

[0058] (1)

[0059] Similarly, on the sphere and In , we get the following relationship:

[0060] (2)

[0061] From the law of cosines we know that:

[0062] (3)

[0063] make , we can get:

[0064] (4)

[0065] About the geocentric angle The expression is:

[0066] (5)

[0067] Among them, combining equations (2) to (4) gives The expansion of is:

[0068] (6)

[0069] From formula (5) and formula (6), we can get The final expression of is:

[0070] (7)

[0071] The phase difference between the first satellite and the second satellite is constant, let , substituting the geocentric angle The expression of further simplification will eventually be Simplify to independent variable function.

[0072] Will Transformed to contain a single variable To simplify formula (7), we introduce Representing the constant coefficients in the formula, we get:

[0073] (8)

[0074] in:

[0075] ;

[0076] To find the minimum distance between the first satellite and the second satellite during their orbit, that is, to find the geocentric angle The minimum value of , the problem of finding the minimum distance between the first satellite and the second satellite is transformed into finding The maximum value of . Using the sum-difference-product formula, we get The value range of .

[0077] In the formula Expand and use Substituting the constant coefficients in the expansion, we obtain:

[0078] (9)

[0079] in:

[0080] ;

[0081] Transform formula (9) into:

[0082] (10)

[0083] At this point, the geocentric angle between any first satellite and any second satellite expressed by orbital elements is obtained through geometric analysis.

[0084] For parameters Function , , when the unit vector With vector When parallel and in the same direction, can obtain the maximum value. At this time, the vector It can be expressed as:

[0085] (11)

[0086] At this particular point, the function have:

[0087] (12)

[0088] Apply this result to solve for the maximum value From the problem we can get:

[0089] (13)

[0090] Similarly, The minimum value of is as follows:

[0091] (14)

[0092] Derivation and calculation of geocentric angle The maximum value of the satellite is obtained, and the maximum distance expression and the minimum distance expression between the first satellite and the second satellite are calculated according to the geocentric angle.

[0093] Specifically, the maximum distance between the first satellite and the second satellite at the same orbital altitude on a circular orbit is expressed as:

[0094] ;

[0095] Indicates the maximum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite.

[0096] The radius of the Earth , track height , first orbit inclination , the first latitude argument , right ascension of the first ascending node , the second orbital inclination , second latitude argument and the right ascension of the second ascending node , substituting into the above maximum distance expression, we can get the maximum distance threshold between the first satellite and the second satellite.

[0097] The minimum distance between the first satellite and the second satellite at the same orbital altitude in a circular orbit is expressed as:

[0098] ;

[0099] in, Indicates the minimum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite.

[0100] The radius of the Earth , track height , first orbit inclination , the first latitude argument , right ascension of the first ascending node , the second orbital inclination , second latitude argument and the right ascension of the second ascending node , substituting into the above minimum distance expression, we can get the minimum distance threshold between the first satellite and the second satellite.

[0101] In order to verify the correctness of the method proposed in this scheme, simulation analysis was carried out, and the simulation parameters were set as follows: Satellite 1: orbit altitude 500km, eccentricity 0, first orbit inclination 50°, first ascending node right ascension 0°, first latitude amplitude 0°; Satellite 2: orbit altitude 500km, eccentricity 0, second orbit inclination 40°, second ascending node right ascension 20°, second latitude amplitude 10°. The maximum distance threshold between the two satellites calculated by the method in this scheme is 3524.28km, and the minimum distance threshold is 3205.50km. The simulation results using STK (Satellite Tool Kit, a professional satellite orbit analysis and simulation software) are as follows: the maximum distance threshold between the two satellites is 3524.35km, and the minimum distance threshold is 3205.58 km, as shown in Figure 2. Figure 3 A schematic diagram of a curve showing the change in the distance between two satellites is shown.

[0102] Through the above verification, it can be seen that compared with the STK simulation method, the error of the maximum distance threshold of this scheme is , the error of the minimum distance threshold is: Compared with the above, the error between the two is small and the results are relatively consistent, which can show the correctness of the calculation method of this scheme.

[0103] The above-mentioned satellite inter-satellite distance determination method studies a calculation and analysis method for the maximum distance threshold and the minimum distance threshold between any two satellites in the same orbital layer. The calculation results can be used as constraints for collision avoidance in the design of giant constellations. First, a three-dimensional model of the spatial position of any two satellites in the same shell is established in the geocentric inertial coordinate system, and based on orbital dynamics and geometry-related theories, the expression of the geocentric angle of the two satellites represented by the basic orbital elements is derived, and through a series of simplification and transformation steps, the maximum distance between the two satellites in the full cycle is finally obtained. If the minimum distance between any two satellites in the constellation is greater than the minimum distance threshold for satellite operation, internal collisions within the constellation can be avoided to a large extent.

[0104] The above satellite inter-satellite distance calculation method, based on the satellite space geometric relationship, gives an analytical formula for calculating the maximum inter-satellite distance between two satellites in the same shell, and the analytical formula is expressed in terms of satellite basic orbit elements, providing a convenient and effective calculation method. This method has reference value for the configuration design of giant constellations. In particular, it has reference value for the establishment of collision avoidance constraints in the design of low-orbit giant constellations. This method also has reference value for the design of inter-satellite links in heterogeneous constellation configurations.

[0105] The embodiment of the present invention provides a device for determining the inter-satellite distance of satellites, such as Figure 4As shown, the device includes: an acquisition module 50, used to acquire a first orbital inclination, a first latitude argument and a first ascending node right ascension of a first satellite, and to acquire a second orbital inclination, a second latitude argument and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; a determination module 51, used to determine a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument and the second ascending node right ascension and a pre-constructed target distance expression.

[0106] The inter-satellite distance determination device of the above-mentioned satellites only needs to obtain the orbital inclination, latitude argument and ascending node right ascension corresponding to the first satellite and the second satellite respectively, and the maximum distance threshold and the minimum distance threshold corresponding to the first satellite and the second satellite can be calculated through the target distance expression, which makes the calculation more simple and efficient.

[0107] Furthermore, the target distance expression includes: a maximum distance expression and a minimum distance expression.

[0108] Furthermore, the determination module is also used to: obtain the radius of the earth, and the orbital altitudes of the first satellite and the second satellite; substitute the earth radius, orbital altitude, first orbital inclination, first latitude argument, first ascending node right ascension, second orbital inclination, second latitude argument, and second ascending node right ascension into a maximum distance expression to obtain a maximum distance threshold between the first satellite and the second satellite; substitute the earth radius, orbital altitude, first orbital inclination, first latitude argument, first ascending node right ascension, second orbital inclination, second latitude argument, and second ascending node right ascension into a minimum distance expression to obtain a minimum distance threshold between the first satellite and the second satellite.

[0109] Furthermore, the maximum distance expression is:

[0110] ;

[0111] Indicates the maximum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ;

[0112] ;

[0113] ;

[0114] ;

[0115] ;

[0116] ;

[0117] ;

[0118] The second latitude argument Argument of first latitude The difference between represents the first orbit inclination; represents the inclination of the second orbit; Indicates the right ascension of the second ascending node Right Ascension of First Ascending Node The difference between .

[0119] Furthermore, the minimum distance expression is:

[0120] ;

[0121] in, Indicates the minimum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ;

[0122] ;

[0123] ;

[0124] ;

[0125] ;

[0126] ;

[0127] ;

[0128] The second latitude argument Argument of first latitude The difference between represents the first orbit inclination; represents the inclination of the second orbit; Indicates the right ascension of the second ascending node Right Ascension of First Ascending Node The difference between .

[0129] Furthermore, the first satellite and the second satellite have the same orbital altitude.

[0130] Furthermore, the eccentricity corresponding to the first satellite and the eccentricity corresponding to the second satellite are both zero.

[0131] The implementation principle and technical effects of the satellite inter-satellite distance determination device provided in the embodiment of the present invention are the same as those of the aforementioned satellite inter-satellite distance determination method embodiment. For the sake of brief description, for matters not mentioned in the embodiment of the satellite inter-satellite distance determination device, reference may be made to the corresponding contents in the aforementioned satellite inter-satellite distance determination method embodiment.

[0132] The embodiment of the present invention further provides an electronic device, see Figure 5 As shown, the electronic device includes a processor 130 and a memory 131. The memory 131 stores machine executable instructions that can be executed by the processor 130. The processor 130 executes the machine executable instructions to implement the above-mentioned method for determining the inter-satellite distance of satellites.

[0133] Further, Figure 5 The electronic device shown further includes a bus 132 and a communication interface 133 , and the processor 130 , the communication interface 133 and the memory 131 are connected via the bus 132 .

[0134] The memory 131 may include a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk storage. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 133 (which may be wired or wireless), and the Internet, wide area network, local area network, metropolitan area network, etc. may be used. The bus 132 may be an ISA bus, a PCI bus, or an EISA bus, etc. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 5 Only one bidirectional arrow is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0135] The processor 130 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the hardware integrated logic circuit or software instructions in the processor 130. The above processor 130 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present invention can be implemented or executed. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor, etc. The steps of the method disclosed in conjunction with the embodiments of the present invention can be directly embodied as a hardware decoding processor for execution, or a combination of hardware and software modules in the decoding processor for execution. The software module may be located in a storage medium mature in the art, such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory 131, and the processor 130 reads the information in the memory 131 and completes the steps of the method of the above embodiment in combination with its hardware.

[0136] An embodiment of the present invention also provides a machine-readable storage medium, which stores machine-executable instructions. When the machine-executable instructions are called and executed by a processor, the machine-executable instructions prompt the processor to implement the above-mentioned method for determining the inter-satellite distance of satellites. The specific implementation can be found in the method embodiment, which will not be repeated here.

[0137] The computer program product of the satellite inter-satellite distance determination method, device and electronic device provided in the embodiments of the present invention includes a computer-readable storage medium storing program code, and the instructions included in the program code can be used to execute the method described in the previous method embodiment. The specific implementation can be referred to the method embodiment, which will not be repeated here.

[0138] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc., which can store program codes.

[0139] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for determining the inter-satellite distance of satellites, characterized in that: The method comprises: Acquire a first orbital inclination, a first latitude argument, and a first ascending node right ascension of a first satellite, and acquire a second orbital inclination, a second latitude argument, and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; Determine a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument, the second ascending node right ascension and a pre-constructed target distance expression; The target distance expression includes: a maximum distance expression and a minimum distance expression; The maximum distance expression is: ； Indicates the maximum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ; ； ； ； ； ； ； is the second latitude argument The first latitude argument The difference between represents the first orbital inclination; represents the inclination of the second orbit; The right ascension of the second ascending node is The right ascension of the first ascending node The difference between .

2. The method according to claim 1, characterized in that The step of determining a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite based on the first orbital inclination, the first latitude argument, the first ascending node right ascension, the second orbital inclination, the second latitude argument, the second ascending node right ascension and a pre-constructed target distance expression comprises: Obtaining the radius of the earth, and the orbital altitudes of the first satellite and the second satellite; Substituting the earth radius, the orbital altitude, the first orbital inclination, the first latitude argument, the right ascension of the first ascending node, the second orbital inclination, the second latitude argument, and the right ascension of the second ascending node into the maximum distance expression to obtain a maximum distance threshold between the first satellite and the second satellite; Substitute the earth radius, the orbital altitude, the first orbital inclination, the first latitude argument, the right ascension of the first ascending node, the second orbital inclination, the second latitude argument, and the right ascension of the second ascending node into the minimum distance expression to obtain the minimum distance threshold between the first satellite and the second satellite.

3. The method according to claim 1, characterized in that The minimum distance expression is: ； in, Indicates the minimum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ; ； ； ； ； ； ； is the second latitude argument The first latitude argument The difference between represents the first orbital inclination; represents the inclination of the second orbit; The right ascension of the second ascending node is The right ascension of the first ascending node The difference between .

4. The method according to claim 1, characterized in that: The first satellite and the second satellite have the same orbital altitude.

5. The method according to claim 1, characterized in that: The eccentricity corresponding to the first satellite and the eccentricity corresponding to the second satellite are both zero.

6. A device for determining the inter-satellite distance of a satellite, characterized in that: The device comprises: an acquisition module, configured to acquire a first orbital inclination, a first latitude argument, and a first ascending node right ascension of a first satellite, and acquire a second orbital inclination, a second latitude argument, and a second ascending node right ascension of a second satellite; wherein the first satellite and the second satellite belong to the same satellite shell; a determination module, configured to determine a maximum distance threshold and a minimum distance threshold between the first satellite and the second satellite based on the first orbital inclination, the first latitude argument, the right ascension of the first ascending node, the second orbital inclination, the second latitude argument, the right ascension of the second ascending node, and a pre-constructed target distance expression; The target distance expression includes: a maximum distance expression and a minimum distance expression; The maximum distance expression is: ； Indicates the maximum distance threshold; represents the radius of the Earth; represents the orbital altitudes of the first satellite and the second satellite; ; ； ； ； ； ； ； is the second latitude argument The first latitude argument The difference between represents the first orbital inclination; represents the inclination of the second orbit; The right ascension of the second ascending node is The right ascension of the first ascending node The difference between .

7. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores machine executable instructions that can be executed by the processor, and the processor executes the machine executable instructions to implement the method for determining the inter-satellite distance of satellites as described in any one of claims 1 to 5.

8. A machine-readable storage medium, characterized in that: The machine-readable storage medium stores machine-executable instructions. When the machine-executable instructions are called and executed by a processor, the machine-executable instructions prompt the processor to implement the method for determining the inter-satellite distance of satellites as described in any one of claims 1-5.

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