Method and device for determining multi-beam coverage area of satellite

Abstract

The invention relates to a satellite multi-beam coverage area determination method and a satellite multi-beam coverage area determination device. The method comprises the following steps: determining an upper limit of the number of multi-beam coverage layers of a satellite according to a sub-satellite half cone angle and a satellite-borne multi-beam antenna angle resolution; determining at least one beam layer number according to the upper limit of the multi-beam coverage layer number; determining a target beam layer number from the at least one beam layer number according to the path loss difference of the adjacent beam layers before the beam gain compensation of each layer and the path loss difference of the adjacent beam layers after the beam gain compensation of each layer in each beam layer number, and determining the optimal beam width of each layer of beam corresponding to the target beam layer number; and determining the multi-beam coverage area of the satellite according to the target beam layer number and the optimal beam width of each layer of beam corresponding to the target beam layer number. By implementing the embodiment of the invention, the balance effect of the gain difference of each beam on the path transmission loss difference can be better, so that the equal flux degree in the beam can be improved.

Description

Technical Field

[0001] The present disclosure relates to the field of satellite-borne antenna technology, and in particular to a method and device for determining a satellite multi-beam coverage area. Background Art

[0002] Although the satellite multi-beam coverage pattern is similar to that of the ground cellular network, the coverage radius of a single satellite can usually reach hundreds to thousands of kilometers, and the surface curvature of the earth cannot be ignored. To serve the same area of ​​ground, low-orbit communication satellites require a larger beam scanning angle (such as sub-satellite viewing angle or sub-satellite cone angle) range than high-orbit communication satellites. Therefore, for low-orbit satellites, the transmission loss of each sub-satellite scanning angle path varies greatly, and the signal power flux received by different users or the same user at different times is uneven, which increases the difficulty of beam switching and the overhead of power control, and reduces the communication capacity and operation stability of the low-orbit satellite system. Summary of the invention

[0003] The present disclosure provides a method and device for determining a satellite multi-beam coverage area.

[0004] In a first aspect, an embodiment of the present disclosure provides a method for determining a satellite multi-beam coverage area, including:

[0005] Determining a subsatellite semi-cone angle of a satellite and determining an angular resolution of an onboard multi-beam antenna of the satellite;

[0006] Determining an upper limit of the number of multi-beam coverage layers of the satellite according to the lower semi-conical angle of the satellite and the angular resolution of the onboard multi-beam antenna;

[0007] Determining at least one beam layer number according to the upper limit of the multi-beam coverage layer number;

[0008] For each of the beam layers, determining the path loss difference between adjacent beam layers in the beam layers before beam gain compensation, and determining the path loss difference between adjacent beam layers in the beam layers after beam gain compensation;

[0009] Determining a target beam layer number from the at least one beam layer number according to a path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layer number and a path loss difference between adjacent beam layers after beam gain compensation in each layer of the beam layer number, and determining an optimal beam width of each layer of beams corresponding to the target beam layer number;

[0010] The multi-beam coverage area of ​​the satellite is determined according to the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number.

[0011] In combination with some embodiments of the first aspect, in some embodiments, determining the path loss difference of adjacent beam layers in the number of beam layers before beam gain compensation of each layer includes: determining at least one group of beam widths corresponding to the number of beam layers according to the lower semi-cone angle of the satellite, each group of the beam widths including the beam widths of each layer of beams in the number of beam layers; for each group of the beam widths in the number of beam layers, using free space propagation loss to determine the path loss of each layer of beams in the number of beam layers before beam gain compensation; and determining the path loss difference of adjacent beam layers in the number of beam layers before beam gain compensation according to the path loss of each layer of beams before beam gain compensation.

[0012] In combination with some embodiments of the first aspect, in some embodiments, determining the path loss difference between adjacent beam layers in the number of beam layers after beam gain compensation of each layer includes: determining the path loss of each layer of beams after beam gain compensation based on the path loss of each layer of beams in the number of beam layers before beam gain compensation and the beam gain of each layer of beams; determining the path loss difference between adjacent beam layers in the number of beam layers after beam gain compensation based on the path loss of each layer of beams after beam gain compensation.

[0013] In combination with some embodiments of the first aspect, in some embodiments, the target beam layer number is determined from the at least one beam layer number according to the path loss difference of adjacent beam layers in the beam layer number before beam gain compensation and the path loss difference of adjacent beam layers in the beam layer number after beam gain compensation, including: determining the average path loss difference corresponding to the beam layer number according to the path loss difference of adjacent beam layers in the beam layer number before beam gain compensation and the path loss difference of adjacent beam layers in the beam layer number after beam gain compensation; and determining the beam layer number with the smallest average path loss difference in the at least one beam layer number as the target beam layer number.

[0014] In combination with some embodiments of the first aspect, in some embodiments, determining the optimal beam width of each layer of beams corresponding to the target beam layer number includes: based on the average path loss difference corresponding to the target beam layer number, determining the optimal beam width of each layer of beams corresponding to the target beam layer number from at least one group of beam widths corresponding to the target beam layer number.

[0015] In combination with some embodiments of the first aspect, in some embodiments, determining the average path loss difference corresponding to the number of beam layers according to the path loss difference of adjacent beam layers in each layer of the beam layers before beam gain compensation and the path loss difference of adjacent beam layers after beam gain compensation includes: determining a first weight corresponding to the path loss difference of adjacent beam layers before beam gain compensation; determining a second weight corresponding to the path loss difference of adjacent beam layers after beam gain compensation; determining the average path loss difference corresponding to the number of beam layers according to the path loss difference of adjacent beam layers in each layer of the beam layers before beam gain compensation, the path loss difference of adjacent beam layers after beam gain compensation, the first weight and the second weight.

[0016] In combination with some embodiments of the first aspect, in some embodiments, the calculation formula of the average path loss difference corresponding to the number of beam layers is expressed as follows:

[0017]

[0018] Among them, J m is the average path loss difference corresponding to the number of beam layers m, l i is the path loss of the i-th beam in the beam layer m before beam gain compensation, L i is the path loss of the i-th beam in the beam layer w after beam gain compensation, w 1 is the first weight corresponding to the path loss difference of adjacent beam layers before beam gain compensation, w 2 is a second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation.

[0019] In combination with some embodiments of the first aspect, in some embodiments, the path loss of the i-th layer beam before beam gain compensation is obtained in the following manner: determining the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth based on the orbital altitude of the satellite, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; determining the propagation distance of the i-th layer beam between the satellite and the earth based on the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; determining the path loss of the i-th layer beam before beam gain compensation based on the propagation distance of the i-th layer beam between the satellite and the earth and the center frequency of the multi-beam antenna.

[0020] In combination with some embodiments of the first aspect, in some embodiments, the path loss of the i-th layer beam after beam gain compensation is obtained in the following manner: determining the beam gain of the i-th layer beam based on a first parameter and the beam width of the i-th layer beam; the first parameter is related to the antenna structure and working state of the multi-beam antenna; determining the path loss of the i-th layer beam after beam gain compensation based on the path loss of the i-th layer beam before beam gain compensation and the beam gain of the i-th layer beam.

[0021] In combination with some embodiments of the first aspect, in some embodiments, determining the satellite's subsatellite semi-cone angle includes: determining the satellite's orbital altitude and determining the minimum elevation angle of ground equipment; determining the satellite's subsatellite semi-cone angle based on the satellite's orbital altitude, the minimum elevation angle of ground equipment and the radius of the earth.

[0022] In combination with some embodiments of the first aspect, in some embodiments, determining the angular resolution of the satellite's onboard multi-beam antenna includes: using the beam width determined by the maximum aperture of the multi-beam antenna and the wavelength of the multi-beam antenna's operating frequency at the maximum scanning angle to determine the angular resolution of the satellite's onboard multi-beam antenna; wherein the maximum scanning angle is equal to the satellite's lower half-cone angle.

[0023] In combination with some embodiments of the first aspect, in some embodiments, determining the upper limit of the number of multi-beam coverage layers of the satellite based on the lower half-cone angle of the satellite and the angular resolution of the onboard multi-beam antenna includes: dividing the lower half-cone angle of the satellite and the angular resolution of the onboard multi-beam antenna and rounding it down in sequence, and determining the obtained integer as the upper limit of the number of multi-beam coverage layers of the satellite.

[0024] In a second aspect, an embodiment of the present disclosure provides a device for determining a satellite multi-beam coverage area, including:

[0025] A first determination module is used to determine the lower half cone angle of the satellite and determine the angular resolution of the satellite's onboard multi-beam antenna;

[0026] A second determination module is used to determine the upper limit of the number of multi-beam coverage layers of the satellite according to the lower semi-cone angle of the satellite and the angular resolution of the onboard multi-beam antenna;

[0027] A third determination module is used to determine at least one beam layer number according to the upper limit of the multi-beam coverage layer number;

[0028] A fourth determination module is used to determine, for each of the beam layers, a path loss difference between adjacent beam layers before beam gain compensation of each layer in the beam layer, and determine a path loss difference between adjacent beam layers after beam gain compensation of each layer in the beam layer;

[0029] a fifth determination module, configured to determine a target beam layer number from the at least one beam layer number according to a path loss difference between adjacent beam layers before beam gain compensation of each layer in the beam layer number and a path loss difference between adjacent beam layers after beam gain compensation of each layer, and determine an optimal beam width of each layer corresponding to the target beam layer number;

[0030] The sixth determination module is used to determine the multi-beam coverage area of ​​the satellite according to the target beam layer number and the optimal beam width of each layer corresponding to the target beam layer number.

[0031] In combination with some embodiments of the second aspect, in some embodiments, the fourth determination module is specifically used to: determine at least one group of beam widths corresponding to the beam layer number according to the lower semi-cone angle of the satellite, each group of the beam widths including the beam widths of each layer of beams in the beam layer number; for each group of the beam widths in the beam layer number, use free space propagation loss to determine the path loss of each layer of beams in the beam layer number before beam gain compensation; determine the path loss difference of adjacent beam layers in the beam layer number before beam gain compensation based on the path loss of each layer of beams before beam gain compensation.

[0032] In combination with some embodiments of the second aspect, in some embodiments, the fourth determination module is specifically used to: determine the path loss of each layer of beams in the number of beam layers after beam gain compensation based on the path loss of each layer of beams in the number of beam layers before beam gain compensation and the beam gain of each layer of beams; determine the path loss difference of adjacent beam layers in the number of beam layers after beam gain compensation based on the path loss of each layer of beams in the number of beam layers.

[0033] In combination with some embodiments of the second aspect, in some embodiments, the fifth determination module is specifically used to: determine the average path loss difference corresponding to the beam layer number based on the path loss difference of adjacent beam layers before beam gain compensation of each layer in the beam layer number and the path loss difference of adjacent beam layers after beam gain compensation of each layer; determine the beam layer number with the smallest average path loss difference among at least one beam layer number as the target beam layer number.

[0034] In combination with some embodiments of the second aspect, in some embodiments, the fifth determination module is specifically used to: based on the average path loss difference corresponding to the target beam layer number, determine the optimal beam width of each layer of beam corresponding to the target beam layer number from at least one group of beam widths corresponding to the target beam layer number.

[0035] In combination with some embodiments of the second aspect, in some embodiments, the fifth determination module is specifically used to: determine a first weight corresponding to the path loss difference between adjacent beam layers before beam gain compensation; determine a second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation; and determine the average path loss difference corresponding to the number of beam layers based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layers, the path loss difference between adjacent beam layers after beam gain compensation in each layer, the first weight and the second weight.

[0036] In combination with some embodiments of the second aspect, in some embodiments, the calculation formula of the average path loss difference corresponding to the number of beam layers is expressed as follows:

[0037]

[0038] Among them, J m is the average path loss difference corresponding to the number of beam layers m, l i is the path loss of the i-th beam in the beam layer m before beam gain compensation, L i is the path loss of the i-th beam in the beam layer m after beam gain compensation, w 1 is the first weight corresponding to the path loss difference of adjacent beam layers before beam gain compensation, w 2 is a second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation.

[0039] In combination with some embodiments of the second aspect, in some embodiments, the path loss of the i-th layer beam before beam gain compensation is obtained in the following manner: determining the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth based on the orbital altitude of the satellite, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; determining the propagation distance of the i-th layer beam between the satellite and the earth based on the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; determining the path loss of the i-th layer beam before beam gain compensation based on the propagation distance of the i-th layer beam between the satellite and the earth and the center frequency of the multi-beam antenna.

[0040] In combination with some embodiments of the second aspect, in some embodiments, the path loss of the i-th layer beam after beam gain compensation is obtained in the following manner: determining the beam gain of the i-th layer beam based on a first parameter and the beam width of the i-th layer beam; the first parameter is related to the antenna structure and working state of the multi-beam antenna; determining the path loss of the i-th layer beam after beam gain compensation based on the path loss of the i-th layer beam before beam gain compensation and the beam gain of the i-th layer beam.

[0041] In combination with some embodiments of the second aspect, in some embodiments, the first determination module is specifically used to: determine the orbital altitude of the satellite and determine the minimum elevation angle of the ground equipment; determine the lower half cone angle of the satellite based on the orbital altitude of the satellite, the minimum elevation angle of the ground equipment and the radius of the earth.

[0042] In combination with some embodiments of the second aspect, in some embodiments, the first determination module is specifically used to: determine the angular resolution of the satellite's onboard multi-beam antenna using the beam width determined by the maximum aperture of the multi-beam antenna and the wavelength of the multi-beam antenna's operating frequency at the maximum scanning angle; wherein the maximum scanning angle is equal to the satellite's lower half-cone angle.

[0043] In combination with some embodiments of the second aspect, in some embodiments, the second determination module is specifically used to: divide and round down the satellite lower half-cone angle and the satellite-borne multi-beam antenna angular resolution in sequence, and determine the obtained integer as the upper limit of the number of multi-beam coverage layers of the satellite.

[0044] In a third aspect, an embodiment of the present disclosure provides an electronic device, comprising: one or more processors; wherein the electronic device is used to execute the satellite multi-beam coverage area determination method described in the first aspect above.

[0045] In a fourth aspect, an embodiment of the present disclosure provides a storage medium storing instructions. When the instructions are executed on an electronic device, the electronic device executes the satellite multi-beam coverage area determination method described in the first aspect.

[0046] In a fifth aspect, an embodiment of the present disclosure provides a computer program product. When the computer program product is executed by an electronic device, the electronic device executes the satellite multi-beam coverage area determination method described in the first aspect.

[0047] The technical solution provided by the embodiments of the present disclosure may have the following beneficial effects:

[0048] By combining the path loss difference of adjacent beam layers before and after beam gain compensation, the target beam layer number and the optimal beam width of each beam layer corresponding to the target beam layer number are determined. This can better balance the gain differences of each beam on the path transmission loss differences, thereby improving the degree of equal flux within the beam, thereby reducing the difficulty of beam switching and the overhead of power control, and improving the communication capacity and operation stability of the low-orbit satellite system.

[0049] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0051] Figure 1 A schematic diagram of the architecture of a satellite communication system provided in an embodiment of the present disclosure.

[0052] Figure 2 The present invention is a flowchart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment.

[0053] Figure 3 The present invention is a flowchart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment.

[0054] Figure 4 A schematic diagram of multi-beam layered coverage shown in an embodiment of the present disclosure.

[0055] Figure 5 The present invention is a flowchart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment.

[0056] Figure 6 The present invention is a flowchart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment.

[0057] Figure 7 The present invention is a block diagram of a device for determining a satellite multi-beam coverage area according to an exemplary embodiment.

[0058] Figure 8 It is a block diagram of an electronic device according to an exemplary embodiment. DETAILED DESCRIPTION

[0059] The embodiments of the present disclosure are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present disclosure, and should not be construed as limitations on the present disclosure. In the description of the present disclosure, unless otherwise specified, " / " means or, for example, A / B can mean A or B; "and / or" in this article is merely a description of the association relationship of associated objects, indicating that three relationships may exist, for example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone.

[0060] The terms used in the disclosed embodiments are only for the purpose of describing specific embodiments, and are not intended to limit the disclosed embodiments. The singular forms "a", "an" and "the" used in the disclosed embodiments and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings.

[0061] It should be understood that although the terms first, second, third, etc. may be used to describe various information in the disclosed embodiments, these information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of the disclosed embodiments, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the words "if" and "if" as used herein may be interpreted as "at" or "when" or "in response to determination".

[0062] Embodiments of the present disclosure are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present disclosure, and should not be construed as limiting the present disclosure.

[0063] In order to better understand the satellite multi-beam coverage area determination method provided by the embodiment of the present disclosure, the communication system to which the embodiment of the present disclosure is applicable is first described below.

[0064] See also Figure 1 , Figure 1 The following is a schematic diagram of the architecture of a satellite communication system provided by an embodiment of the present disclosure. Figure 1 As shown, the satellite communication system may include but is not limited to a satellite device (also called a satellite). Figure 1 The number and form of the devices shown are for example only and do not constitute a limitation on the embodiments of the present disclosure. In actual applications, two or more satellites may be included. Figure 1 The satellite communication system shown includes two satellites 101 as an example.

[0065] It should be noted that the technical solution of the embodiment of the present disclosure can be applied to various satellite communication systems.

[0066] The satellite 101 in the embodiment of the present disclosure may be a satellite device in a low-orbit satellite communication system, or may be a satellite device in a medium-orbit satellite communication system, or may be a satellite device in a high-orbit satellite communication system. The satellite 101 in the embodiment of the present disclosure is an entity for transmitting or receiving signals. Among them, the satellite communication system in the embodiment of the present disclosure includes but is not limited to Iridium, Maritime Satellite, OneWeb, Globalstar, Starlink, Tiantong, etc.

[0067] It can be understood that the satellite communication system described in the embodiment of the present disclosure is for the purpose of more clearly illustrating the technical solution of the embodiment of the present disclosure, and is not sufficient to constitute a limitation on the technical solution provided by the embodiment of the present disclosure. A person skilled in the art can know that with the evolution of the system architecture and the emergence of new business scenarios, the technical solution provided by the embodiment of the present disclosure is also applicable to similar technical problems.

[0068] The satellite multi-beam coverage area determination method and device provided by the present disclosure are described in detail below in conjunction with the accompanying drawings.

[0069] Figure 2 It is a flow chart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment. It should be noted that the method involved in the embodiments of the present disclosure can be applied to electronic devices. In some embodiments, the electronic device can be a satellite 101 in a satellite communication system, or it can also be a ground device in a satellite communication system. Exemplarily, the electronic device can be a ground device in a satellite communication system. After determining the multi-beam coverage area of ​​the satellite, the corresponding parameters (such as the number of target beam layers and the optimal beam width of each layer of beams corresponding to the number of target beam layers) can be sent to the satellite 101, so that the satellite 101 can perform beamforming based on the parameters. Exemplarily, if the satellite 101 has a strong computing power, the method can also be applied to the satellite 101, and the multi-beam coverage area of ​​the satellite 101 can be determined by the satellite 101, and then beamforming can be performed based on the multi-beam coverage area.

[0070] like Figure 2 As shown, the method may include but is not limited to the following steps.

[0071] In step 201, the lower half cone angle of the satellite is determined, and the angular resolution of the satellite's onboard multi-beam antenna is determined.

[0072] In some embodiments, the satellite's lower half-cone angle may be calculated based on the satellite's orbital altitude, the minimum elevation angle of the ground equipment, and the radius of the earth. Exemplarily, the satellite's orbital altitude and the minimum elevation angle of the ground equipment may be determined, and the satellite's lower half-cone angle may be determined based on the satellite's orbital altitude, the minimum elevation angle of the ground equipment, and the radius of the earth.

[0073] In some embodiments, the satellite's lower half-cone angle may be determined by the satellite's orbital altitude and the minimum elevation angle of the ground equipment. Exemplarily, the calculation formula of the satellite's lower half-cone angle may be expressed as follows:

[0074]

[0075] Among them, β is the satellite's lower semi-cone angle, R is the radius of the earth, h is the satellite's orbital altitude, and θ is the minimum elevation angle of the ground equipment.

[0076] Optionally, in some embodiments, the angular resolution of the satellite's onboard multi-beam antenna can be determined according to the satellite's lower semi-conical angle. In one possible implementation, the angular resolution of the satellite's onboard multi-beam antenna is determined by using a beam width determined by the maximum aperture of the multi-beam antenna and the wavelength of the multi-beam antenna's operating frequency at the maximum scanning angle; wherein the maximum scanning angle is equal to the lower semi-conical angle.

[0077] Exemplarily, the angular resolution of the satellite's onboard multi-beam antenna may adopt a beam width determined by the maximum aperture of the multi-beam antenna and the operating wavelength (such as the wavelength of the multi-beam antenna's operating frequency) at a scanning angle equal to the lower half cone angle of the satellite. For example, the calculation formula for the angular resolution of the satellite's onboard multi-beam antenna may be expressed as follows:

[0078]

[0079] Among them, Δβ is the angular resolution of the satellite's onboard multi-beam antenna, λ is the wavelength of the multi-beam antenna's operating frequency, D is the maximum aperture of the multi-beam antenna, and k is the beam width. For example, under the beam width definition of half-power full width, k can be 0.886.

[0080] In step 202, the upper limit of the number of multi-beam coverage layers of the satellite is determined according to the lower half cone angle of the satellite and the angular resolution of the onboard multi-beam antenna.

[0081] In some embodiments, the satellite lower half cone angle and the satellite-borne multi-beam antenna angular resolution may be divided and rounded down in sequence, and the resulting integer may be determined as the upper limit of the number of multi-beam coverage layers of the satellite. Exemplarily, the calculation formula for the upper limit of the number of multi-beam coverage layers of the satellite may be expressed as follows:

[0082]

[0083] Where M is the upper limit of the satellite's multi-beam coverage layer number, is the floor function.

[0084] In some embodiments, the satellite lower half cone angle and the satellite-borne multi-beam antenna angular resolution may be divided and rounded up in sequence, and the resulting integer may be determined as the upper limit of the number of multi-beam coverage layers of the satellite. Exemplarily, the calculation formula for the upper limit of the number of multi-beam coverage layers of the satellite may be expressed as follows:

[0085]

[0086] Where M is the upper limit of the satellite's multi-beam coverage layer number, is the ceiling function.

[0087] In step 203, at least one beam layer number is determined according to the upper limit of the multi-beam coverage layer number.

[0088] In some embodiments, the value range of the number of beam layers can be determined based on the upper limit of the number of multi-beam coverage layers, and then one or more beam layers can be obtained. Exemplarily, based on the upper limit of the number of multi-beam coverage layers, the value range of the number of beam layers can be determined to be "a range not less than 2 and not greater than M", for example, the value range of the number of beam layers is greater than or equal to 2 and less than or equal to M, and one or more beam layers are selected from the value range, for example, the beam layer number can be represented by m.

[0089] In step 204, for each beam layer number, the path loss difference between adjacent beam layers in the beam layer number before beam gain compensation is determined, and the path loss difference between adjacent beam layers in the beam layer number after beam gain compensation is determined.

[0090] Exemplarily, for each beam layer number m within the range of not less than 2 and not greater than M (i.e., the upper limit of the number of multi-beam coverage layers), the path loss difference between adjacent beam layers in the beam layer number m before beam gain compensation of each layer can be determined, and the path loss difference between adjacent beam layers in the beam layer number m after beam gain compensation of each layer can be determined.

[0091] For example, assuming that the number of beam layers selected from a range of not less than 2 and not greater than M (i.e., the upper limit of the number of multi-beam coverage layers) is 3 and 4, then for the number of beam layers is 3, the path loss difference of adjacent beam layers before beam gain compensation of each layer in the 3 beam layers is determined, and the path loss difference of adjacent beam layers after beam gain compensation of each layer in the 3 beam layers is determined. For the number of beam layers is 4, the path loss difference of adjacent beam layers before beam gain compensation of each layer in the 4 beam layers is determined, and the path loss difference of adjacent beam layers after beam gain compensation of each layer in the 4 beam layers is determined.

[0092] In step 205, a target beam layer number is determined from at least one beam layer number based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layer number and the path loss difference between adjacent beam layers after beam gain compensation in each layer of the beam layer number, and the optimal beam width of each layer of beam corresponding to the target beam layer number is determined.

[0093] In some embodiments, the average path loss difference corresponding to the beam layer number can be determined based on the path loss difference between adjacent beam layers in each beam layer before beam gain compensation and the path loss difference between adjacent beam layers in each beam layer after beam gain compensation; the beam layer number with the smallest average path loss difference in at least one beam layer number is determined as the target beam layer number.

[0094] In a possible implementation, the path loss difference between adjacent beam layers in each beam layer before beam gain compensation and the path loss difference between adjacent beam layers in each beam layer after beam gain compensation can be summed and averaged, and the obtained value is determined as the average path loss difference corresponding to the beam layer.

[0095] In another possible implementation, the path loss difference of adjacent beam layers before beam gain compensation in each layer of beam layers and the path loss difference of adjacent beam layers after beam gain compensation in each layer may be weighted, such as weighted summing and then averaging, and the obtained value is determined as the average path loss difference corresponding to the beam layer. Alternatively, the average path loss difference corresponding to the beam layer may be determined in other ways, which is not limited in the present disclosure and will not be described in detail.

[0096] For example, assuming that the number of beam layers selected from a range of not less than 2 and not greater than M (i.e., the upper limit of the number of multi-beam coverage layers) is 3 and 4, if the average path loss difference corresponding to the beam layer number 3 is less than the average path loss difference corresponding to the beam layer number 4, then the beam layer number 3 is determined as the target beam layer number, that is, the target beam layer number is 3. If the average path loss difference corresponding to the beam layer number 4 is less than the average path loss difference corresponding to the beam layer number 3, then the beam layer number 4 is determined as the target beam layer number, that is, the target beam layer number is 4. If the average path loss difference corresponding to the beam layer number 3 is equal to the average path loss difference corresponding to the beam layer number 4, then the beam layer number 3 or 4 is determined as the target beam layer number, that is, the target beam layer number can be 3 or 4.

[0097] In some embodiments, after determining the target beam layer number, the optimal beam width of each layer of beams corresponding to the target beam layer number can be determined according to the average path loss difference corresponding to the target beam layer number. Exemplarily, the beam width used to calculate the average path loss difference corresponding to the target beam layer number can be determined as the optimal beam width of each layer of beams corresponding to the target beam layer number. For example, if the target beam layer number is 3, the beam widths used to calculate the average path loss difference corresponding to the target beam layer number are β , β , and β , respectively. 1 , β 2 and β 3 , then β 1 , β 2 and β 3 Determine the optimal beam width of each beam layer in the three beam layers, such as β 1 is the optimal beam width of the first layer among the three beam layers, β 2 is the optimal beam width of the second layer among the three beam layers, β 3 is the optimal beam width of the third layer among the three beam layers.

[0098] In step 206, the multi-beam coverage area of ​​the satellite is determined according to the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number.

[0099] Exemplarily, after obtaining the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number, the multi-beam coverage area of ​​the satellite can be determined.

[0100] In the above embodiment, the path loss difference of adjacent beam layers before each layer of beam gain compensation and the path loss difference of adjacent beam layers after each layer of beam gain compensation are combined to determine the target beam layer number and the optimal beam width of each layer of beam corresponding to the target beam layer number. This can make the balancing effect of the difference in beam gain on the difference in path transmission loss better, thereby improving the degree of equal flux within the beam, thereby reducing the difficulty of beam switching and the overhead of power control, and improving the communication capacity and operation stability of the low-orbit satellite system.

[0101] Figure 3 FIG. 1 is a flow chart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment. It should be noted that the method involved in the embodiment of the present disclosure can be applied to electronic devices. Figure 3 As shown, the method may include but is not limited to the following steps.

[0102] In step 301, the lower half cone angle of the satellite is determined, and the angular resolution of the satellite's onboard multi-beam antenna is determined.

[0103] In the embodiments of the present disclosure, the implementation of step 301 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0104] In step 302, the upper limit of the number of multi-beam coverage layers of the satellite is determined according to the lower half cone angle of the satellite and the angular resolution of the onboard multi-beam antenna.

[0105] In the embodiments of the present disclosure, the implementation of step 302 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0106] In step 303, at least one beam layer number is determined according to the upper limit of the multi-beam coverage layer number.

[0107] In the embodiments of the present disclosure, the implementation of step 303 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0108] In step 304, for each beam layer number, at least one group of beam widths corresponding to the beam layer number is determined according to the lower half cone angle of the satellite, and each group of beam widths includes the beam widths of each layer of beams in the beam layer number.

[0109] In some embodiments, at least one group of beam widths corresponding to the number of beam layers may be determined based on the satellite's lower semi-cone angle and the preset conditions of the beam widths. That is, each group of beam widths corresponding to the number of beam layers satisfies the preset conditions of the beam widths.

[0110] In one possible implementation, the preset conditions for the beam width may include but are not limited to at least one of the following: the outer beam is narrower than the inner beam (that is, the beam width of the outer beam is smaller than the beam width of the inner beam); the sum of the beam widths of all beam layers in the beam layer is equal to the lower half-cone angle of the satellite.

[0111] Exemplarily, the preset conditions of the beam width may include: 2β 1 >β 2 >…>β m >Δβ; Among them, β i is the beam width of the i-th layer of beams in the beam layer number m, 1≤i≤m, Δβ is the angular resolution of the satellite-borne multi-beam antenna, and β is the lower half cone angle of the satellite. Based on the preset condition, one or more groups of beam widths corresponding to the beam layer number m can be determined, wherein the beam widths of each layer of beams in each group of beam widths meet the preset condition.

[0112] In step 305, for each group of beam widths in the beam layer number, the free space propagation loss is used to determine the path loss of each layer of beams in the beam layer number before beam gain compensation.

[0113] In some embodiments, the path loss of each layer of beams in the beam layer before gain compensation can be determined according to the propagation distance of each layer of beams in the beam layer between the satellite and the ground and the center frequency of the multi-beam antenna.

[0114] In some embodiments, the propagation distance of each layer of beams between the satellite and the ground can be determined by using the angle between the outer edge of each layer of beams in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude of the satellite, the radius of the earth and the scanning angle of the outer edge of the corresponding beam.

[0115] Exemplarily, taking the i-th layer of beams in the beam layer number m as an example, the angle between the outer edge of the i-1th layer of beams in the ground coverage area and the sub-satellite point relative to the center of the earth can be determined based on the orbital altitude of the satellite, the radius of the earth and the scanning angle of the outer edge of the i-1th layer of beams; the propagation distance of the i-th layer of beams between the satellite and the earth can be determined based on the angle between the outer edge of the i-1th layer of beams in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude, the radius of the earth and the scanning angle of the outer edge of the i-1th layer of beams; the path loss of the i-th layer of beams before beam gain compensation can be determined based on the propagation distance of the i-th layer of beams between the satellite and the earth and the center frequency of the multi-beam antenna.

[0116] For example, Figure 4 As shown, according to the satellite's orbital altitude, the earth's radius and the scanning angle of the outer edge of the i-1 layer beam, the following formula (5) is used to determine the angle between the outer edge of the i-1 layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth.

[0117]

[0118] Among them, α i-1 is the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point P relative to the center of the earth O, i = 2, 3, ..., m; R is the radius of the earth, h is the orbital height of the satellite S, β n is the beam width (also called beam angle width) of the nth layer beam. 1 is the half-width of the beam, β i,i≠1 is the full beam width; is the scanning angle of the outer edge of the i-1th layer beam, that is, geometrically, the scanning angle is the sum of the beam widths of the beams from the 1st layer to the i-1th layer.

[0119] like Figure 4 As shown, according to the angle between the outer edge of the i-th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude, the earth radius and the scanning angle of the outer edge of the i-th layer beam, the following formula (6) is used to determine the propagation distance of the i-th layer beam between the satellite and the earth.

[0120]

[0121] Among them, d i is the propagation distance between the satellite and the ground of the i-th layer of beams in the beam layer number m. Exemplarily, for the first layer of beams in the beam layer number m, the propagation distance between the satellite and the ground of the first layer of beams is the orbital altitude of the satellite; for the i-th layer of beams in the beam layer number m (i=2,3,…,m), the propagation distance between the satellite and the ground of the i-th layer of beams in the beam layer number m is determined by the above formula (6) according to the angle between the outer edge of the ground coverage area of ​​the i-1-th layer of beams and the sub-satellite point relative to the center of the earth, the radius of the earth and the scanning angle of the outer edge of the i-1-th layer of beams, and the unit can be kilometers (km).

[0122] Exemplarily, after obtaining the propagation distance of the i-th layer beam between the satellite and the ground, the propagation distance of the i-th layer beam between the satellite and the ground and the center frequency of the multi-beam antenna (such as in GHz) can be used to calculate the path loss of the i-th layer beam before beam gain compensation using the following formula (7).

[0123] l i =92.44+20lgd i +20lgf (7)

[0124] Among them, l i is the path loss of the i-th beam in beam layer m before beam gain compensation, d i is the propagation distance of the i-th layer beam between the satellite and the ground, f is the center frequency of the multi-beam antenna, and lg is the logarithmic function with base 10.

[0125] In step 306, the path loss difference of adjacent beam layers before beam gain compensation in each layer of the beam layer is determined according to the path loss of each layer of beam before beam gain compensation.

[0126] Exemplarily, the following formula (8) may be used to calculate the path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layer number.

[0127] Δl=(l i -l i+1 ) (8)

[0128] Among them, l i+1 is the path loss of the i+1th beam in beam layer m before beam gain compensation, l i is the path loss of the i-th beam in beam layer number m before beam gain compensation, and Δl is the path loss difference between adjacent beam layers (i-th layer and i+1-th layer) before beam gain compensation of the i-th beam in beam layer number m.

[0129] In step 307, the path loss of each layer of beams after beam gain compensation is determined according to the path loss of each layer of beams in the beam layer before beam gain compensation and the beam gain of each layer of beams.

[0130] In some embodiments, the beam gain of the i-th layer of beams may be determined based on the first parameter and the beam width of the i-th layer of beams; the first parameter is related to the antenna structure and working state of the multi-beam antenna. The path loss of the i-th layer of beams after beam gain compensation is determined based on the path loss of the i-th layer of beams before beam gain compensation and the beam gain of the i-th layer of beams.

[0131] Exemplarily, the beam gain of the i-th layer beam can be calculated according to the first parameter and the beam width of the i-th layer beam using the following formula (9).

[0132]

[0133] Among them, G i is the beam gain of the i-th beam in the beam layer m, β i is the beam width of the i-th beam in the beam layer m, η A is a first parameter, and the first parameter may be a parameter determined by the antenna structure and working state of the multi-beam antenna. lg is a logarithmic function with base 10.

[0134] Exemplarily, the path loss of the i-th layer beam before beam gain compensation and the beam gain of the i-th layer beam can be subtracted, and the difference obtained is determined as the path loss of the i-th layer beam after beam gain compensation. For example, the path loss L of the i-th layer beam after beam gain compensation is i = l i -G i .

[0135] In step 308, the path loss difference of adjacent beam layers after beam gain compensation in each layer of the beam layer is determined according to the path loss of each layer of beam after beam gain compensation.

[0136] Exemplarily, the following formula (8) may be used to calculate the path loss difference between adjacent beam layers after beam gain compensation of each layer in the beam layer number.

[0137] ΔL=(L i -L i+1 ) (8)

[0138] Among them, L i+1 is the path loss of the i+1th layer of beam in beam layer m after beam gain compensation, L i is the path loss of the i-th beam in beam layer m after beam gain compensation, and ΔL is the path loss difference between adjacent beam layers (i-th layer and i+1-th layer) after beam gain compensation of the i-th beam in beam layer m.

[0139] In step 309, a target beam layer number is determined from at least one beam layer number based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layer number and the path loss difference between adjacent beam layers after beam gain compensation in each layer of the beam layer number, and the optimal beam width of each layer of beam corresponding to the target beam layer number is determined.

[0140] In the embodiments of the present disclosure, step 309 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0141] In step 310, the multi-beam coverage area of ​​the satellite is determined according to the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number.

[0142] In the embodiments of the present disclosure, step 310 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0143] By implementing the embodiments of the present disclosure, for each beam layer number, at least one group of beam widths corresponding to the beam layer number is determined according to the lower half cone angle of the satellite. For each group of beam widths of the beam layer number, the path loss difference of adjacent beam layers before beam gain compensation of each layer in the beam layer number is calculated using the group of beam widths, and the path loss difference of adjacent beam layers after beam gain compensation of each layer in the beam layer number is calculated. Then, according to the path loss difference of adjacent beam layers before beam gain compensation of each layer in the beam layer number and the path loss difference of adjacent beam layers after beam gain compensation of each layer, the target beam layer number can be determined from at least one beam layer number, and then the optimal beam width of each layer of beam corresponding to the target beam layer number is determined. That is, in the process of determining the multi-beam coverage area of ​​the satellite, by optimizing the search for both the beam layer number and the beam width, the balancing effect of the difference in the gain of each beam on the difference in the path transmission loss can be better, thereby improving the degree of equal flux within the beam.

[0144] Figure 5 FIG. 1 is a flow chart of a method for determining a satellite multi-beam coverage area according to an exemplary embodiment. It should be noted that the method involved in the embodiment of the present disclosure can be applied to electronic devices. Figure 5 As shown, the method may include but is not limited to the following steps.

[0145] In step 501, the lower half cone angle of the satellite is determined, and the angular resolution of the satellite's onboard multi-beam antenna is determined.

[0146] In the embodiments of the present disclosure, the implementation of step 501 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0147] In step 502, the upper limit of the number of multi-beam coverage layers of the satellite is determined according to the lower half cone angle of the satellite and the angular resolution of the onboard multi-beam antenna.

[0148] In the embodiments of the present disclosure, the implementation of step 502 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0149] In step 503, at least one beam layer number is determined according to the upper limit of the multi-beam coverage layer number.

[0150] In the embodiments of the present disclosure, the implementation of step 503 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0151] In step 504, for each beam layer number, the path loss difference between adjacent beam layers in the beam layer number before beam gain compensation is determined, and the path loss difference between adjacent beam layers in the beam layer number after beam gain compensation is determined.

[0152] In the embodiments of the present disclosure, the implementation of step 504 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0153] In step 505, the average path loss difference corresponding to the beam layer number is determined according to the path loss difference of adjacent beam layers before beam gain compensation in each layer of the beam layer number and the path loss difference of adjacent beam layers after beam gain compensation in each layer of the beam layer number.

[0154] In some embodiments, a first weight corresponding to the path loss difference between adjacent beam layers before beam gain compensation is determined; a second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation is determined; and an average path loss difference corresponding to the number of beam layers is determined based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layers, the path loss difference between adjacent beam layers after beam gain compensation in each layer, the first weight, and the second weight.

[0155] Exemplarily, a weighted sum is taken based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of beam layers, the path loss difference between adjacent beam layers after beam gain compensation in each layer, the first weight and the second weight, and then the average is calculated. The obtained value is determined as the average path loss difference corresponding to the beam layer number.

[0156] Exemplarily, the calculation formula of the average path loss difference corresponding to the number of beam layers is expressed as follows:

[0157]

[0158] Among them, J mis the average path loss difference corresponding to the number of beam layers m, l i is the path loss of the i-th beam in the beam layer m before beam gain compensation, L i is the path loss of the i-th beam in the beam layer m after beam gain compensation, w 1 is the first weight corresponding to the path loss difference of adjacent beam layers before beam gain compensation, w 2 is the second weight corresponding to the path loss difference of adjacent beam layers after beam gain compensation. As an example, the first weight and the second weight are both greater than or equal to 0 and less than or equal to 1, and the sum of the first weight and the second weight is equal to 1, such as 0≤w 1 ,w 2 ≤1 and w 1 +w 2 =1.

[0159] Exemplarily, the path loss of the i-th layer beam before beam gain compensation can be calculated by the above formula (7). For optional implementation methods, please refer to the optional implementation methods of the above step 305 and related descriptions, which will not be repeated here.

[0160] Exemplarily, the path loss of the i-th layer beam after beam gain compensation can be calculated by the above formula (7). For optional implementation methods, please refer to the optional implementation methods of the above step 307 and related descriptions, which will not be repeated here.

[0161] In step 506, the beam layer number with the smallest average path loss difference among at least one beam layer number is determined as the target beam layer number.

[0162] For example, if the number of at least one beam layer is 2, and it is assumed that the beam layers selected from the range of not less than 2 and not greater than M (i.e., the upper limit of the number of multi-beam coverage layers) are 3 and 4, if the average path loss difference corresponding to the beam layer number 3 is less than the average path loss difference corresponding to the beam layer number 4, then the beam layer number 3 is determined as the target beam layer number, that is, the target beam layer number is 3. If the average path loss difference corresponding to the beam layer number 4 is less than the average path loss difference corresponding to the beam layer number 3, then the beam layer number 4 is determined as the target beam layer number, that is, the target beam layer number is 4. If the average path loss difference corresponding to the beam layer number 3 is equal to the average path loss difference corresponding to the beam layer number 4, then the beam layer number 3 or 4 is determined as the target beam layer number, that is, the target beam layer number can be 3 or 4.

[0163] In step 507, based on the average path loss difference corresponding to the target beam layer number, the optimal beam width of each layer of beams corresponding to the target beam layer number is determined from at least one group of beam widths corresponding to the target beam layer number.

[0164] Exemplarily, the optimal beam width of each layer of beams corresponding to the target beam layer number is the beam width of each layer of beams used when calculating the average path loss difference corresponding to the target beam layer number.

[0165] For example, the target beam layer number m corresponds to two sets of beam widths. For example, the first set of beam widths includes the beam widths of each layer of beams in the target beam layer number m, which is expressed as follows: 11 ,β 12 ,…,β 1m ; The second set of beam widths includes the beam widths of each layer of the target beam layer m, which is expressed as follows β 21 ,β 22 ,…,β 2m Assume that the average path loss difference corresponding to the target beam layer number m is calculated using β 11 ,β 12 ,…,β 1m Calculated, then β 11 ,β 12 ,…,β 1m That is, the optimal beam width of each layer of beam corresponding to the target beam layer number m. Assume that the average path loss difference corresponding to the target beam layer number m is calculated using β 21 ,β 22 ,…,β 2m Calculated, then β 21 ,β 22 ,…,β 2m That is, it is the optimal beam width of each layer of beam corresponding to the target beam layer number m.

[0166] In step 508, the multi-beam coverage area of ​​the satellite is determined according to the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number.

[0167] In the embodiments of the present disclosure, step 508 may be implemented in any of the above embodiments, which is not limited here and will not be described in detail.

[0168] In order to facilitate those skilled in the art to more clearly understand the present disclosure, Figure 6 The present disclosure is described.

[0169] For example, Figure 6 As shown, step 1: determine the satellite's lower semi-cone angle β; determine the satellite-borne multi-beam antenna angular resolution Δβ; determine the upper limit M of the multi-beam coverage layer according to the lower semi-cone angle β and the satellite-borne multi-beam antenna angular resolution Δβ. For example,

[0170] Step 2: For each beam layer number m within the range of not less than 2 and not greater than M, determine the average path loss difference corresponding to the beam layer number m based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of beam layer m and the path loss difference between adjacent beam layers after beam gain compensation in each layer. Determine the beam layer number with the smallest average path loss difference in at least one beam layer number as the target beam layer number. Exemplarily, first set the beam layer number m to 2, take at least one set of beam widths (such as 2 sets of beam widths) corresponding to the beam layer number m being 2, each set of beam widths includes the beam widths of each layer of beams when the beam layer number m is 2, and the beam widths of each layer of beams in each set of beam widths may be partially the same or completely different. Calculate the average path loss difference corresponding to the beam layer number m being 2. Add 1 to the number of beam layers m. If the number of beam layers m is not greater than M, continue to select at least one set of beam widths (such as 2 sets of beam widths) corresponding to the time when the number of beam layers m is m+1, calculate the corresponding average path loss difference when the number of beam layers m is m+1, and return to the execution step of "add 1 to the number of beam layers m" until the number of beam layers m is greater than M.

[0171] Step 3: Determine the beam layer number m with the smallest average path loss difference as the target beam layer number, and determine the beam width group used when calculating the minimum average path loss difference as the optimal beam width of each layer of beams corresponding to the target beam layer number.

[0172] By implementing the embodiments of the present disclosure, in the process of equal flux coverage design of multi-beam antennas, both the number of beam layers and the beam width are optimized and searched; for each beam layer number, the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number are determined in combination with the path loss difference of adjacent beam coverage layers before and after beam gain compensation. This can achieve a better balancing effect of the gain differences of each beam on the path transmission loss differences, thereby improving the degree of equal flux within the beam, thereby reducing the difficulty of beam switching and the overhead of power control, and improving the communication capacity and operation stability of the low-orbit satellite system.

[0173] Figure 7 FIG. 1 is a block diagram of a device for determining a satellite multi-beam coverage area according to an exemplary embodiment. Figure 7 The device includes a first determination module 701, a second determination module 702, a third determination module 703, a fourth determination module 704, a fifth determination module 705 and a sixth determination module 706.

[0174] The first determination module 701 is used to determine the lower half cone angle of the satellite and determine the angular resolution of the satellite's onboard multi-beam antenna.

[0175] The second determination module 702 is used to determine the upper limit of the number of multi-beam coverage layers of the satellite according to the lower half cone angle of the satellite and the angular resolution of the satellite-borne multi-beam antenna.

[0176] The third determination module 703 is used to determine at least one beam layer number according to the upper limit of the multi-beam coverage layer number.

[0177] The fourth determination module 704 is used to determine, for each beam layer number, the path loss difference between adjacent beam layers in the beam layer number before beam gain compensation, and determine the path loss difference between adjacent beam layers in the beam layer number after beam gain compensation.

[0178] The fifth determination module 705 is used to determine the target beam layer number from at least one beam layer number according to the path loss difference of adjacent beam layers before beam gain compensation in each layer of the beam layer number and the path loss difference of adjacent beam layers after beam gain compensation in each layer, and determine the optimal beam width of each layer corresponding to the target beam layer number.

[0179] The sixth determination module 706 is used to determine the multi-beam coverage area of ​​the satellite according to the target beam layer number and the optimal beam width of each layer corresponding to the target beam layer number.

[0180] In some embodiments, the fourth determination module 704 is specifically used to: determine at least one group of beam widths corresponding to the beam layer number according to the satellite's lower semi-cone angle, each group of beam widths including the beam widths of each layer of beams in the beam layer number; for each group of beam widths in the beam layer number, use free space propagation loss to determine the path loss of each layer of beams in the beam layer number before beam gain compensation; determine the path loss difference of adjacent beam layers in the beam layer number before beam gain compensation based on the path loss of each layer of beams before beam gain compensation.

[0181] In some embodiments, the fourth determination module 704 is specifically used to: determine the path loss of each layer of beams after beam gain compensation based on the path loss of each layer of beams in the beam layer number before beam gain compensation and the beam gain of each layer of beams; determine the path loss difference of adjacent beam layers after beam gain compensation in each layer of beam layers in the beam layer number according to the path loss of each layer of beams after beam gain compensation.

[0182] In some embodiments, the fifth determination module 705 is specifically used to: determine the average path loss difference corresponding to the beam layer number based on the path loss difference of adjacent beam layers before beam gain compensation in each layer and the path loss difference of adjacent beam layers after beam gain compensation in each layer; determine the beam layer number with the smallest average path loss difference in at least one beam layer number as the target beam layer number.

[0183] In some embodiments, the fifth determination module 705 is specifically used to determine the optimal beam width of each layer of beams corresponding to the target beam layer number from at least one group of beam widths corresponding to the target beam layer number based on the average path loss difference corresponding to the target beam layer number.

[0184] In some embodiments, the fifth determination module 705 is specifically used to: determine the first weight corresponding to the path loss difference between adjacent beam layers before beam gain compensation; determine the second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation; and determine the average path loss difference corresponding to the number of beam layers based on the path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layer number, the path loss difference between adjacent beam layers after beam gain compensation in each layer, the first weight and the second weight.

[0185] In some embodiments, the calculation formula of the average path loss difference corresponding to the number of beam layers is expressed as follows:

[0186]

[0187] Among them, J m is the average path loss difference corresponding to the number of beam layers m, l i is the path loss of the i-th beam in the beam layer m before beam gain compensation, L i is the path loss of the i-th beam in the beam layer m after beam gain compensation, w 1 is the first weight corresponding to the path loss difference of adjacent beam layers before beam gain compensation, w 2 It is the second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation.

[0188] In some embodiments, the path loss of the i-th layer beam before beam gain compensation is obtained in the following manner: determining the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth based on the orbital altitude of the satellite, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; determining the propagation distance of the i-th layer beam between the satellite and the earth based on the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; determining the path loss of the i-th layer beam before beam gain compensation based on the propagation distance of the i-th layer beam between the satellite and the earth and the center frequency of the multi-beam antenna.

[0189] In some embodiments, the path loss of the i-th layer beam after beam gain compensation is obtained in the following manner: determining the beam gain of the i-th layer beam based on the first parameter and the beam width of the i-th layer beam; the first parameter is related to the antenna structure and working state of the multi-beam antenna; determining the path loss of the i-th layer beam after beam gain compensation based on the path loss of the i-th layer beam before beam gain compensation and the beam gain of the i-th layer beam.

[0190] In some embodiments, the first determination module 701 is specifically used to: determine the orbital altitude of the satellite and determine the minimum elevation angle of the ground equipment; determine the lower half cone angle of the satellite based on the orbital altitude of the satellite, the minimum elevation angle of the ground equipment and the radius of the earth.

[0191] In some embodiments, the first determination module 701 is specifically used to determine the angular resolution of the satellite's onboard multi-beam antenna using a beam width determined by the maximum aperture of the multi-beam antenna and the wavelength of the multi-beam antenna's operating frequency at the maximum scanning angle; wherein the maximum scanning angle is equal to the satellite's lower half-cone angle.

[0192] In some embodiments, the second determination module 702 is specifically used to: divide and round down the satellite lower half cone angle and the satellite-borne multi-beam antenna angular resolution in sequence, and determine the obtained integer as the upper limit of the number of multi-beam coverage layers of the satellite.

[0193] Regarding the device in the above embodiment, the specific manner in which each module performs operations has been described in detail in the embodiment of the method, and will not be elaborated here.

[0194] Figure 8 800 is a block diagram of an electronic device 800 according to an exemplary embodiment. The electronic device 800 may be a satellite device (such as the aforementioned satellite), or a chip, a chip system, or a processor that supports the satellite device to implement the above method. The electronic device 800 may also be a ground device, or a chip, a chip system, or a processor that supports the ground device to implement the above method. The electronic device 800 may be used to implement the method described in the above method embodiment, and the details may refer to the description in the above method embodiment.

[0195] The electronic device 800 may include one or more processors 801. The processor 801 may be a general-purpose processor or a dedicated processor, etc. For example, it may be a baseband processor or a central processing unit. The baseband processor may be used to process the communication protocol and communication data, and the central processing unit may be used to control the communication device (such as a base station, a baseband chip, a terminal device, a terminal device chip, a DU or a CU, etc.), execute a computer program, and process the data of the computer program.

[0196] Optionally, the electronic device 800 may further include one or more memories 802, on which a computer program 804 may be stored, and the processor 801 executes the computer program 804 so that the electronic device 800 performs the method described in the above method embodiment. Optionally, data may also be stored in the memory 802. The electronic device 800 and the memory 802 may be provided separately or integrated together.

[0197] Optionally, the electronic device 800 may further include a transceiver 805 and an antenna 806. The transceiver 805 may be referred to as a transceiver unit, a transceiver, or a transceiver circuit, etc., and is used to implement a transceiver function. The transceiver 805 may include a receiver and a transmitter, the receiver may be referred to as a receiver or a receiving circuit, etc., and is used to implement a receiving function; the transmitter may be referred to as a transmitter or a transmitting circuit, etc., and is used to implement a transmitting function.

[0198] Optionally, the electronic device 800 may further include one or more interface circuits 807. The interface circuit 807 is used to receive code instructions and transmit them to the processor 801. The processor 801 runs the code instructions to enable the electronic device 800 to perform the method described in the above method embodiment.

[0199] In one implementation, the processor 801 may include a transceiver for implementing receiving and sending functions. For example, the transceiver may be a transceiver circuit, an interface, or an interface circuit. The transceiver circuit, interface, or interface circuit for implementing the receiving and sending functions may be separate or integrated. The above-mentioned transceiver circuit, interface, or interface circuit may be used for reading and writing code / data, or the above-mentioned transceiver circuit, interface, or interface circuit may be used for transmitting or delivering signals.

[0200] In one implementation, the processor 801 may store a computer program, which runs on the processor 801 and enables the electronic device 800 to perform the method described in the above method embodiment. The computer program may be fixed in the processor 801, in which case the processor 801 may be implemented by hardware.

[0201] In one implementation, the electronic device 800 may include a circuit that can implement the functions of sending, receiving, or communicating in the aforementioned method embodiments. The processor and transceiver described in the present disclosure may be implemented in an integrated circuit (IC), an analog IC, a radio frequency integrated circuit RFIC, a mixed signal IC, an application specific integrated circuit (ASIC), a printed circuit board (PCB), an electronic device, and the like. The processor and transceiver may also be manufactured using various IC process technologies, such as complementary metal oxide semiconductor (CMOS), N-type metal oxide semiconductor (nMetal-oxide-semiconductor, NMOS), P-type metal oxide semiconductor (positive channelmetal oxide semiconductor, PMOS), bipolar junction transistor (bipolar junction transistor, BJT), bipolar CMOS (BiCMOS), silicon germanium (SiGe), gallium arsenide (GaAs), and the like.

[0202] The communication device described in the above embodiments may be a satellite device (such as the first satellite device or the second satellite device mentioned above), but the scope of the communication device described in the present disclosure is not limited thereto, and the structure of the communication device may not be limited thereto. Figure 8 The communication device may be an independent device or may be part of a larger device. For example, the communication device may be:

[0203] (1) Independent integrated circuit IC, or chip, or chip system or subsystem;

[0204] (2) having a set of one or more ICs, and optionally, the IC set may also include a storage component for storing data and computer programs;

[0205] (3) ASIC, such as modem;

[0206] (4) Modules that can be embedded in other devices;

[0207] (5) Receivers, terminal devices, intelligent terminal devices, cellular phones, wireless devices, handheld devices, mobile units, vehicle-mounted devices, network devices, cloud devices, artificial intelligence devices, etc.;

[0208] (6)Others

[0209] Those skilled in the art may also understand that the various illustrative logical blocks and steps listed in the embodiments of the present disclosure may be implemented by electronic hardware, computer software, or a combination of the two. Whether such functions are implemented by hardware or software depends on the specific application and the design requirements of the entire system. Those skilled in the art may use various methods to implement the functions described for each specific application, but such implementation should not be understood as exceeding the scope of protection of the embodiments of the present disclosure.

[0210] The present disclosure also provides a readable storage medium on which instructions are stored. When the instructions are executed by the processor 801, the functions of any of the above method embodiments are implemented.

[0211] The present disclosure also provides a computer program product, which implements the functions of any of the above method embodiments when executed by the processor 801.

[0212] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented by software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer programs. When the computer program is loaded and executed on a computer, the process or function described in the embodiment of the present disclosure is generated in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer program can be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium. For example, the computer program can be transmitted from a website site, computer, server or data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (digital subscriber line, DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) mode to another website site, computer, server or data center. The computer-readable storage medium can be any available medium that a computer can access or a data storage device such as a server or data center that includes one or more available media integrated. The available medium may be a magnetic medium (eg, a floppy disk, a hard disk, a magnetic tape), an optical medium (eg, a high-density digital video disc (DVD)), or a semiconductor medium (eg, a solid state disk (SSD)).

[0213] Those skilled in the art can understand that the various numerical numbers such as first and second involved in the present disclosure are only used for distinction for convenience of description and are not used to limit the scope of the embodiments of the present disclosure, and also indicate the order of precedence.

[0214] At least one in the present disclosure may also be described as one or more, and a plurality may be two, three, four or more, which is not limited in the present disclosure. In the embodiments of the present disclosure, for a technical feature, the technical features in the technical feature are distinguished by "first", "second", "third", "A", "B", "C" and "D", etc., and there is no order of precedence or size between the technical features described by the "first", "second", "third", "A", "B", "C" and "D".

[0215] The corresponding relationships shown in the tables in the present disclosure can be configured or predefined. The values ​​of the information in each table are only examples and can be configured as other values, which are not limited by the present disclosure. When configuring the corresponding relationship between the information and each parameter, it is not necessarily required to configure all the corresponding relationships illustrated in each table. For example, in the table in the present disclosure, the corresponding relationships shown in some rows may not be configured. For another example, appropriate deformation adjustments can be made based on the above table, such as splitting, merging, etc. The names of the parameters shown in the titles of the above tables can also use other names that can be understood by the communication device, and the values ​​or representations of the parameters can also be other values ​​or representations that can be understood by the communication device. When implementing the above tables, other data structures can also be used, such as arrays, queues, containers, stacks, linear lists, pointers, linked lists, trees, graphs, structures, classes, heaps, hash tables or hash tables.

[0216] The predefined in the present disclosure may be understood as defined, predefined, stored, pre-stored, pre-negotiated, pre-configured, solidified, or pre-burned.

[0217] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this disclosure.

[0218] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0219] The above is only a specific embodiment of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any person skilled in the art who is familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. A method for determining a satellite multi-beam coverage area, characterized in that: include: Determining a subsatellite semi-cone angle of a satellite and determining an angular resolution of an onboard multi-beam antenna of the satellite; Determining an upper limit of the number of multi-beam coverage layers of the satellite according to the lower semi-conical angle of the satellite and the angular resolution of the onboard multi-beam antenna; Determining at least one beam layer number according to the upper limit of the multi-beam coverage layer number; For each of the beam layers, determining the path loss difference between adjacent beam layers in the beam layers before beam gain compensation, and determining the path loss difference between adjacent beam layers in the beam layers after beam gain compensation; Determining a target beam layer number from the at least one beam layer number according to a path loss difference between adjacent beam layers before beam gain compensation in each layer of the beam layer number and a path loss difference between adjacent beam layers after beam gain compensation in each layer of the beam layer number, and determining an optimal beam width of each layer of beams corresponding to the target beam layer number; The multi-beam coverage area of ​​the satellite is determined according to the target beam layer number and the optimal beam width of each layer of beams corresponding to the target beam layer number.

2. The method according to claim 1, characterized in that The determining of the path loss difference of adjacent beam layers before beam gain compensation of each layer in the number of beam layers includes: Determine at least one group of beam widths corresponding to the number of beam layers according to the lower half cone angle of the satellite, each group of beam widths including beam widths of each layer of beams in the number of beam layers; For each group of the beam widths of the beam layers, a free space propagation loss is used to determine the path loss of each layer of beams in the beam layers before beam gain compensation; According to the path loss of each layer of beams before beam gain compensation, the path loss difference of adjacent beam layers in each layer of the beam layers before beam gain compensation is determined.

3. The method according to claim 1 or 2, characterized in that The determining of the path loss difference of adjacent beam layers after beam gain compensation of each layer in the number of beam layers includes: Determining the path loss of each layer of beams after beam gain compensation according to the path loss of each layer of beams in the number of beam layers before beam gain compensation and the beam gain of each layer of beams; According to the path loss of each layer of beams after beam gain compensation, the path loss difference of adjacent beam layers after beam gain compensation in each layer of the beam layers is determined.

4. The method according to claim 1 or 2, characterized in that: The determining a target beam layer number from the at least one beam layer number according to a path loss difference between adjacent beam layers before beam gain compensation of each layer in the beam layer number and a path loss difference between adjacent beam layers after beam gain compensation of each layer, comprises: Determining an average path loss difference corresponding to the number of beam layers according to a path loss difference between adjacent beam layers before beam gain compensation in each layer of the number of beam layers and a path loss difference between adjacent beam layers after beam gain compensation in each layer of the number of beam layers; The beam layer number with the smallest average path loss difference among the at least one beam layer number is determined as the target beam layer number.

5. The method according to claim 4, characterized in that The determining of the optimal beam width of each layer of beams corresponding to the target beam layer number includes: Based on the average path loss difference corresponding to the target beam layer number, the optimal beam width of each layer of beams corresponding to the target beam layer number is determined from at least one group of beam widths corresponding to the target beam layer number.

6. The method according to claim 4, characterized in that The determining, according to the path loss difference of adjacent beam layers before beam gain compensation of each layer in the beam layer number and the path loss difference of adjacent beam layers after beam gain compensation of each layer, an average path loss difference corresponding to the beam layer number includes: Determine a first weight corresponding to a path loss difference between adjacent beam layers before beam gain compensation; Determine a second weight corresponding to a path loss difference between adjacent beam layers after beam gain compensation; The average path loss difference corresponding to the number of beam layers is determined according to the path loss difference of adjacent beam layers before beam gain compensation of each layer in the number of beam layers, the path loss difference of adjacent beam layers after beam gain compensation of each layer, the first weight and the second weight.

7. The method according to claim 4, characterized in that The calculation formula of the average path loss difference corresponding to the number of beam layers is expressed as follows: Among them, J m is the average path loss difference corresponding to the number of beam layers m, l i is the path loss of the i-th beam in the beam layer m before beam gain compensation, L i is the path loss of the i-th beam among the beam layers m after beam gain compensation, w1 is the first weight corresponding to the path loss difference between adjacent beam layers before beam gain compensation, and w2 is the second weight corresponding to the path loss difference between adjacent beam layers after beam gain compensation.

8. The method according to claim 7, characterized in that The path loss of the i-th layer beam before beam gain compensation is obtained in the following way: Determine the angle between the outer edge of the i-1 layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth according to the orbital altitude of the satellite, the radius of the earth and the scanning angle of the outer edge of the i-1 layer beam; Determine the propagation distance of the i-th layer beam between the satellite and the ground according to the angle between the outer edge of the i-1th layer beam in the ground coverage area and the sub-satellite point relative to the center of the earth, the orbital altitude, the radius of the earth and the scanning angle of the outer edge of the i-1th layer beam; According to the propagation distance of the i-th layer of beams between the satellite and the ground and the center frequency of the multi-beam antenna, the path loss of the i-th layer of beams before beam gain compensation is determined.

9. The method according to claim 7, characterized in that The path loss of the i-th layer beam after beam gain compensation is obtained in the following way: Determining the beam gain of the i-th layer of beams according to a first parameter and a beam width of the i-th layer of beams; the first parameter is related to the antenna structure and working state of the multi-beam antenna; The path loss of the i-th layer of beam after beam gain compensation is determined according to the path loss of the i-th layer of beam before beam gain compensation and the beam gain of the i-th layer of beam.

10. The method according to claim 1, characterized in that The method of determining the lower half cone angle of the satellite comprises: Determining the orbital altitude of the satellite and determining the minimum elevation angle of ground equipment; The subsatellite semi-cone angle of the satellite is determined according to the orbital altitude of the satellite, the minimum elevation angle of the ground equipment and the radius of the earth.

11. The method according to claim 1, characterized in that The determining of the angular resolution of the satellite-borne multi-beam antenna comprises: The angular resolution of the satellite-borne multi-beam antenna is determined by using a beam width determined by the maximum aperture of the multi-beam antenna and the wavelength of the operating frequency of the multi-beam antenna at a maximum scanning angle; wherein the maximum scanning angle is equal to the lower semi-cone angle of the satellite.

12. The method according to claim 1, characterized in that The step of determining the upper limit of the number of multi-beam coverage layers of the satellite according to the lower semi-cone angle of the satellite and the angular resolution of the onboard multi-beam antenna comprises: The satellite lower semi-cone angle and the satellite-borne multi-beam antenna angular resolution are divided and rounded down in sequence, and the obtained integer is determined as the upper limit of the number of multi-beam coverage layers of the satellite.

13. A device for determining a satellite multi-beam coverage area, characterized in that: include: A first determination module is used to determine the lower half cone angle of the satellite and determine the angular resolution of the satellite's onboard multi-beam antenna; A second determination module is used to determine the upper limit of the number of multi-beam coverage layers of the satellite according to the lower semi-cone angle of the satellite and the angular resolution of the onboard multi-beam antenna; A third determination module is used to determine at least one beam layer number according to the upper limit of the multi-beam coverage layer number; A fourth determination module is used to determine, for each of the beam layers, a path loss difference between adjacent beam layers before beam gain compensation of each layer in the beam layer, and determine a path loss difference between adjacent beam layers after beam gain compensation of each layer in the beam layer; a fifth determination module, configured to determine a target beam layer number from the at least one beam layer number according to a path loss difference between adjacent beam layers before beam gain compensation of each layer in the beam layer number and a path loss difference between adjacent beam layers after beam gain compensation of each layer, and determine an optimal beam width of each layer corresponding to the target beam layer number; The sixth determination module is used to determine the multi-beam coverage area of ​​the satellite according to the target beam layer number and the optimal beam width of each layer corresponding to the target beam layer number.

14. An electronic device, characterized in that: include: one or more processors; The electronic device is used to execute the satellite multi-beam coverage area determination method described in any one of claims 1-12.

15. A storage medium storing instructions, characterized in that: When the instructions are executed on an electronic device, the electronic device is enabled to execute the satellite multi-beam coverage area determination method according to any one of claims 1 to 12.

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