Method and system for controlling satellite communications

Abstract

A method for controlling satellite communications in which a satellite (202) flies in an orbit (204) above the Earth (206). The method includes providing a first target position (210) on the Earth's surface, determining the satellite's orbit, identifying a first interference restriction area (214) through which the satellite's orbit passes, and determining an elevation angle (δ1, δ2) with respect to the satellite and the first target position. The elevation angle is the angle between the Earth's horizontal plane and a vector pointing from the first target position to the satellite in orbit at a given moment. The method further includes activating a first communications beam (208) from the satellite toward the first target position when the elevation angle is in the range between an activation angle (δ1) and a deactivation angle (δ2). If the first interference restriction area is located ahead of the satellite's motion, the activation angle is smaller than the deactivation angle, and if the first interference restriction area is located behind the satellite's motion, the activation angle is larger than the deactivation angle.

Description

[Technical Field]

[0001] The present disclosure (hereinafter referred to as "this disclosure") relates to a method for controlling satellite communications of a satellite orbiting the Earth. Furthermore, this disclosure relates to a system for controlling satellite communications of a satellite orbiting the Earth. Moreover, this disclosure relates to a computer program product for controlling satellite communications of a satellite orbiting the Earth. Background

[0002] Satellite communications connect one point on the Earth's surface to another, transmitting information (e.g., communications (e.g., 3GPP® mobile communications, television broadcasting, radio broadcasting, satellite phones, satellite internet, telemedicine, distance education), navigation (e.g., Global Positioning System (GPS)), and weather monitoring (e.g., public safety and disaster recovery)) via satellites positioned in space. Satellites typically orbit the Earth at various altitudes and speeds, such as geostationary orbits (where satellites maintain a fixed position relative to the Earth's surface) and low Earth orbits (where satellites are closer to the Earth's surface). Satellites function as relay stations, transmitting signals received from ground transmitters to ground receivers. This enables long-distance communication across remote areas and oceans where land-based communication systems are unavailable or limited. In recent years, satellite access to fifth-generation (5G) and sixth-generation (6G) wireless communication technologies has expanded the coverage of terrestrial networks (which are typically limited to densely populated areas), aiming to provide seamless, global internet connectivity even in remote and harsh environments (such as oceans, deserts, and mountainous regions), bridge the digital divide, and support the development of new technologies and applications. However, it is important to note that the implementation of satellite access to 5G and 6G services is still in its early stages, and technical, economic, and regulatory challenges need to be overcome.

[0003] In particular, 5G and 6G technologies require high bandwidth and low latency to support advanced applications such as mobile broadband, virtual reality, and IoT (Internet of Things). Regulatory authorities and the satellite and terrestrial communications industries are coordinating globally to allocate optimal frequency bands (specific frequency ranges on the electromagnetic spectrum) for 5G or 6G satellite communications. By securing dedicated frequency bands, satellite signals are prevented from being interfered with by other radio frequency (RF) signal sources, enabling the delivery of efficient, high-speed, and reliable wireless services to users worldwide. Dedicated bands must be guaranteed not to cause harmful interference to users of other radio frequency bands. The Radio Regulations of the International Telecommunication Union Telecommunication Sector (ITU-R) define harmful interference as "interference which endangers the functioning of a radionavigation service or of other safety services or seriously degrades, obstructs, or repeatedly interrupts a radiocommunication service operating in accordance with Radio Regulations." Radio communications are shared between ground and satellite systems, either (1) when a terrestrial communication system is the primary user of the frequency band and a satellite communication system is a secondary user of the frequency band, or (2) through cooperative frequency band sharing between primary users of the same frequency band (e.g., extension of a terrestrial network using a satellite network, or partial sharing of the same frequency band by multiple satellites). Interference management techniques control the use of radio spectrum resources so that spectrum users (i.e., satellites, ground stations, UEs, etc.) do not cause harmful interference to each other. Interference management techniques can also optimize the efficient use of radio spectral resources and maintain a fair allocation (manual or automatic) between different parts of the spectrum.However, conventional interference management techniques for spectrum sharing control tend to be inefficient because they often set excessive protection margins (geographic, frequency, time, power level) around the protected (restricted) region.

[0004] In light of these circumstances, it is necessary to overcome the aforementioned shortcomings in existing technologies and equipment related to satellite communication control. Summary

[0005] This disclosure aims to provide a method for controlling satellite communications of satellites orbiting the Earth. This disclosure also aims to provide a system for controlling satellite communications of satellites orbiting the Earth. Furthermore, this disclosure aims to provide a computer program product for controlling satellite communications of satellites orbiting the Earth. The objective of this disclosure is to provide solutions that at least partially overcome the problems encountered in the prior art.

[0006] According to a first aspect, embodiments of the present disclosure provide a method for controlling satellite communications of a satellite orbiting the Earth. The method is: To provide a first target location on the Earth's surface; To determine the orbit of the aforementioned satellite on Earth; Identifying a first interference restriction zone through which the orbit of the aforementioned satellite passes; Determining the elevation angle between the satellite and the first target position, wherein the elevation angle is the angle between the horizontal plane of the Earth and a vector pointing from the first target position to the satellite in orbit at a given moment; When the elevation angle is within the range between the activation angle and the deactivation angle, the first communication beam is activated from the satellite toward the first target position; This includes, however, If the first interference restriction zone is located ahead of the motion of the satellite along the orbit, the activation angle is smaller than the deactivation angle. When the first interference limitation area is located behind the movement of the satellite along the orbit, the deactivation angle is smaller than the activation angle; The method further deactivates the first communication beam when the elevation angle exceeds the deactivation angle; including.

[0007] According to a second aspect, an embodiment of the present disclosure provides a system for controlling satellite communication flying in an orbit on the earth. This system includes a server system, and the server system · Identify the first target position on the earth's surface; · Determine the orbit of the satellite on the earth; · Identify the first interference limitation area through which the orbit of the satellite passes from a limitation area database; · Determine the elevation angle with respect to the satellite and the first target position, where the elevation angle is the angle between the horizontal plane of the earth and the vector pointing from the first target position to the satellite on the orbit at a certain moment, and determine the elevation angle; · Activate the first communication beam from the satellite towards the first target position when the elevation angle is within the range between the activation angle and the deactivation angle; configured as follows, provided that · When the first interference limitation area is located in front of the movement of the satellite along the orbit, the activation angle is smaller than the deactivation angle, · When the first interference limitation area is located behind the movement of the satellite along the orbit, the deactivation angle is smaller than the activation angle; · The server system is further configured to transmit the values of the activation angle and the deactivation angle to the satellite.

[0008] According to a third aspect, an embodiment of the present disclosure provides a computer program product storing program instructions in a non-volatile machine-readable data storage medium. Here, when the program instructions are executed by a processor, the processor is caused to execute the steps of the computer-implemented method of the first aspect.

[0009] Embodiments of the present disclosure substantially solve or at least partially address the aforementioned problems in the prior art, define a radio interference restricted area (i.e., a protection area), and guide wireless communication to a geostationary beam transmission arranged outside the radio interference restricted area or disable a satellite beam, thereby enabling efficient interference restriction in addition to efficient wireless communication. This enables accurate and reliable bypassing of the radio interference restricted area by satellites in orbit.

[0010] Further aspects, advantages, features, and objectives of what is disclosed in this application will become apparent from the detailed description of the accompanying drawings and exemplary embodiments, which are to be construed in conjunction with the appended claims.

[0011] It will also be understood that the features of the present disclosure can be combined in various combinations without departing from the scope defined by the appended claims.

Brief Description of the Drawings

[0012] The above abstract and the following detailed description of exemplary embodiments are better understood when read in conjunction with the accompanying drawings. For the purpose of explaining the present disclosure, an exemplary configuration of the present disclosure is shown in the drawings. However, the present disclosure is not limited to the specific methods and apparatuses disclosed herein. Also, the scales of the drawings are not correct. Similar elements are denoted with the same numbers as much as possible. Hereinafter, embodiments of the present disclosure will be described by way of example with reference to the following drawings. [Figure 1] Steps of a method for controlling satellite communication of a satellite flying in an orbit on the earth are shown according to an embodiment of the present invention. [Figure 2A]A block diagram of the architecture of a system for controlling satellite communications of a satellite orbiting the Earth is shown according to an embodiment of the present invention. [Figure 2B] A block diagram of the architecture of a system including multiple satellites that controls satellite communications of multiple satellites orbiting the Earth is shown according to an embodiment of the present invention. [Figure 3] An embodiment of the present invention illustrates the exemplary motion of a satellite and how the shape of the surrounding region changes as the satellite moves. [Figure 4] An embodiment of the present invention illustrates the stepwise motion of a satellite orbiting the Earth. [Figure 5] An embodiment of the present invention illustrates the stepwise motion of a satellite orbiting the Earth. [Figure 6] This shows the radiation pattern of a satellite communication beam on Earth according to an embodiment of the present invention. [Figure 7] The antenna model geometry according to an embodiment of the present invention is shown. [Figure 8] An embodiment of the present invention illustrates a shared satellite communication scenario between user equipment on a non-terrestrial network (NTN) and a terrestrial network (TN). [Figure 9] A world map showing some areas of the S-band ITU-R frequency allocation according to embodiments of the present invention is shown. Detailed description of the embodiment

[0013] The following detailed description illustrates embodiments of the disclosure and methods by which they may be implemented. While several forms for implementing the disclosure have been disclosed, those skilled in the art will recognize that other forms for implementing the disclosure are also possible.

[0014] According to a first aspect, embodiments of the present disclosure provide a method for controlling satellite communications of a satellite orbiting the Earth. The method is: To provide a first target location on the Earth's surface; To determine the orbit of the aforementioned satellite on Earth; Identifying a first interference restriction zone through which the orbit of the aforementioned satellite passes; Determining the elevation angle between the satellite and the first target position, wherein the elevation angle is the angle between the horizontal plane of the Earth and a vector pointing from the first target position along the orbit of the satellite at a given moment; When the elevation angle is within the range between the activation angle and the deactivation angle, the first communication beam is activated from the satellite toward the first target position; This includes, however, If the first interference restriction zone is located ahead of the motion of the satellite along the orbit, the activation angle is smaller than the deactivation angle. If the first interference restriction zone is located behind the motion of the satellite along the orbit, the deactivation angle is smaller than the activation angle; The method further includes deactivating the first communication beam when the elevation angle exceeds the deactivation angle; Includes.

[0015] According to a second aspect, embodiments of the present disclosure provide a system for controlling satellite communications flying in orbit over the Earth. The system comprises a server system, the server system is Identify the first target location on the Earth's surface; • Determine the orbit of the satellite on Earth; From the restricted area database, identify the first interference restricted area through which the satellite's orbit passes; The objective is to determine the elevation angles (δ1, δ2) between the satellite and the first target position, wherein the elevation angle is the angle between the horizontal plane of the Earth and the vector pointing from the first target position to the satellite in orbit at a given moment; When the elevation angles (δ1, δ2) are within the range between the activation angle (δ1) and the deactivation angle (δ2), the first communication beam is activated from the satellite toward the first target position; It is configured in such a way, however, If the first interference restriction zone is located ahead of the motion of the satellite along the orbit, the activation angle is smaller than the deactivation angle. If the first interference restriction zone is located behind the motion of the satellite along the orbit, the deactivation angle is smaller than the activation angle; The server system is further configured to transmit the activation angle value and the deactivation angle value to the satellite.

[0016] According to a third aspect, embodiments of the present disclosure provide a computer program product in which program instructions are stored in a non-volatile machine-readable data storage medium, wherein, when executed by a processor, the program instructions cause the processor to perform the steps of the computer implementation method of the first aspect.

[0017] This disclosure provides the aforementioned method, system, and computer program product for improving radio communications of satellites orbiting the Earth while limiting harmful interference to other primary or secondary systems (specifically, ground base stations, user equipment (UEs), satellites, etc.) that share the frequency band allocated for such radio communications. The method makes it possible to define interference-restricted areas where interference from radio transmissions of non-terrestrial networks (NTNs) is lower than the normal operating area of ​​the NTNs. Furthermore, the method controls satellite communication beams using the defined interference-restricted areas such that coverage ahead of the interference-restricted areas is generated mainly by satellites moving toward the interference-restricted areas, and coverage behind the interference-restricted areas is generated mainly by satellites located behind the interference-restricted areas.

[0018] A method for controlling satellite communications of a satellite orbiting the Earth. A satellite is an artificial object placed in orbit around the Earth along a specific path or route (orbit) for the purpose of observing the Earth from space. Depending on the embodiment, the satellite's orbit defines its velocity, altitude, and direction of motion. Here, "controlling satellite communications of a satellite" means managing and coordinating the satellite's communication mechanisms so that the satellite functions effectively in space as it orbits the Earth and relays information to and from ground stations (i.e., base stations and mobile units). Depending on the embodiment, controlling satellite communications may include, but is not limited to, monitoring the satellite's orbit and position, adjusting the satellite's orientation and power consumption, and sending and receiving information with the satellite. Controlling satellite communications may also include adjusting the satellite's antenna and its antenna pattern for proper communication with base stations.

[0019] Satellite antennas are essential components of satellite communication systems, used to transmit and receive radio waves or other electromagnetic waves to and from the ground (i.e., ground stations or base stations) or other satellites. The number, size, and shape of antennas vary depending on the type of satellite and the frequency of the signals they process. Some satellites may have multiple antennas used for different purposes, such as transmitting and receiving signals at different frequencies or communicating with ground stations.

[0020] In some embodiments, a satellite antenna maintains one or more Earth-fixed beams. Typically, an Earth-fixed beam refers to a type of satellite communications antenna that is fixed to a specific location on the Earth's surface as the satellite passes over that location. Earth-fixed beam antennas are designed to maintain a fixed beam relative to a specific location on Earth, enabling a permanent connection to a specific location on the ground (such as a receiving station or mobile vehicle). To maintain signal transmission as the satellite and / or Earth moves, the satellite antenna may need to continuously adjust its direction. The satellite antenna may also need to continuously adjust its radio pattern. Alternatively, the satellite antenna may be positioned to point towards the center of the Earth, and its antenna pattern may continuously shift as the satellite's position changes.

[0021] In this regard, the method includes providing a first target location on the Earth's surface, where the first target location is a specific point on the Earth's ground station, i.e., a geographical area on the Earth, or a base station or mobile vehicle in that geographical area, configured to send and receive information or signals with a satellite antenna. In this regard, the first target location is positioned on the Earth's surface to directly receive satellite communications by maintaining a constant connection with the satellite antenna. The first target location typically includes an antenna that connects (receives and transmits) to the satellite antenna using a radio frequency (RF) link. In some embodiments, the satellite antenna is an Earth-fixed beam antenna, and therefore the first target location is an Earth-fixed beam receiver that receives satellite communications from the Earth-fixed beam antenna. Radio transmission from an Earth-fixed beam antenna is called transmission or Earth-fixed beam transmission. In Earth-fixed beam transmission, the satellite attempts to maintain the center of its beam within the first target location on the Earth, as long as the first target location is in its line of sight.

[0022] Furthermore, the method includes determining the satellite's orbit above the Earth. Typically, the satellite's position and orbit can be determined, for example, using a network of tracking stations that monitor the satellite's orbit above the Earth. This information (orbital parameters) is used to calculate the satellite's position, velocity, direction, i.e., its orbit. This orbital information includes various factors such as the satellite's altitude and velocity, the gravity acting on the satellite, as well as the Earth's rotation and the presence of other space objects that may affect the satellite's orbit. This information is also shared with the satellite, allowing its server system to use its onboard system to calculate its current position and velocity, as well as the forces acting on the satellite, such as gravity and atmospheric drag. The satellite's orbit can be determined by mathematical models and simulations, which are important for predicting the satellite's future position and maintaining a stable orbit.

[0023] Typically, the first target location first establishes a connection with the satellite and then initiates communication with the satellite's antenna, such as sending and receiving data like images, videos, and scientific measurements. The amount of data that can be transmitted is determined by the satellite's capabilities and the RF link bandwidth. Depending on the embodiment, the first target location may be equipped with special equipment for encrypting or decrypting data or performing other processing tasks.

[0024] In some embodiments, the first communication beam is kept pointed towards the first target position by adjusting the direction of the satellite's antenna radiation pattern as a function of the orbit (moment in orbit). As the satellite orbits the Earth, the direction of the antenna radiation pattern changes relative to the Earth. Therefore, in order to maintain stable communication between the satellite's antenna and the first target position, the satellite's antenna needs to be directed towards the first target position such that the first communication beam remains pointed towards the first target position, preferably towards its center.

[0025] In some embodiments, the frequency and signal strength of the communication beam can be adjusted to optimize data transmission and reception, and the antenna can be tilted or rotated to adjust the antenna's radiation pattern direction to compensate for changes in the satellite's position as it moves through orbit. The antenna's radiation pattern direction can be controlled electronically by adjusting the frequency and power to the antenna elements without making any mechanical changes to the antenna structure itself. In some embodiments, such adjustments can be automated using machine learning or artificial intelligence tools. Alternatively, such adjustments may be proposed by the user of the satellite's server system. To maintain a stable connection with a first target location, the satellite's antenna radiation pattern direction is adjusted in real time as a function of the orbit using information corresponding to the first target location on the Earth's surface and the satellite's orbit.

[0026] The method further includes identifying a first interference-restricted area through which the satellite's orbit passes. Here, "interference-restricted area" is defined as an area where interference from non-terrestrial network (NTN) radio transmissions is lower than the normal operating area of ​​NTN. However, terrestrial networks (TN), such as cellular networks, may also cause radio transmissions within or around the interference-restricted area. The satellite orbit does not necessarily pass directly over the interference-restricted area, but may pass alongside it. Here, "first interference-restricted area" refers to one of several identified interference-restricted areas.

[0027] Interference restrictions can stem from regional differences in radio regulations within the International Telecommunication Union Radio Sector (ITU-R). Specifically, these are Region 1 (Europe, the Middle East, and Africa (EMEA)), Region 2 (the Americas and the Caribbean), and Region 3 (Asia and Oceania). Different countries have different laws, regulations, and frequency band deployment schedules, and other types of interference restrictions exist for various reasons. For example, these include avoiding mutual interference between different radio systems and prioritizing target radio systems. Identifying interference restriction zones located in satellite orbit is crucial to avoid potential adverse effects on existing terrestrial networks.

[0028] Depending on the embodiment, the method enables the storage of information corresponding to identified interference-restricted areas in a database, which is transmitted to a server system of a satellite flying in orbit through an interference-restricted area. Beneficially, identifying interference-restricted areas allows satellite operators to ensure that their satellite systems operate reliably and efficiently without interference from or from other radio systems. Such uninterrupted satellite operation is crucial for critical satellite applications such as navigation, communications, and weather forecasting.

[0029] Furthermore, the method includes determining the elevation angle between the satellite and a first target position. This elevation angle is the angle between the Earth's horizontal plane and a vector pointing from the first target position to the orbiting satellite at a given moment. One way to define the elevation angle (EA) is to associate it with the angle formed between the horizontal plane and the (virtual) line of sight (vector) arising from the (radio communication) beam connecting the satellite and the first target position. Thus, the elevation angle is an acute angle between the horizontal plane and the vector. The elevation angle takes values ​​from 0 to 90 degrees. 0 degrees refers to the state where the satellite is on the horizon. The elevation angle is 90 degrees when the satellite is at the nadir. The nadir refers to the state where the first target position is on the straight line connecting the center of the Earth and the satellite. As the satellite moves along its orbit above the target position, the value of the elevation angle increases from 0 to a maximum of 90 degrees. As the satellite passes the target position and disappears below the horizon, the elevation angle decreases from its maximum value of 90 degrees towards 0 degrees. As the satellite orbits, the EA (Elevation Angle) is formed from the center of the first target location so that the satellite's antenna tracks the center of the first target location within the satellite's field of view. The maximum elevation angle reaches 90 degrees only when the satellite's orbit passes the first target location. When the orbit passes alongside the first target location, the maximum elevation angle is less than 90 degrees.

[0030] The angle of elevation relative to the target position also depends on the deviation of the trajectory from the target position. For example, if the trajectory deviates significantly to the left or right of the target position, the angle of elevation is adjusted based on standard geometry. For instance, if the trajectory passes directly over the target position, the angle of elevation is 40 degrees, but if the trajectory deviates 200 km to the left of the target position, the angle of elevation becomes 30 degrees.

[0031] Moving towards a first interference restriction zone, and with the first target position in front of the first interference restriction zone, can generate more active communication beams than moving away from the first interference restriction zone.

[0032] Similarly, when moving towards a first interference restriction zone, and the first target position is behind the first interference restriction zone, fewer active communication beams can be generated than when moving away from the first interference restriction zone.

[0033] The method of this disclosure enables the creation of non-terrestrial network (NTN) coverage around an interference-restricted area on Earth. In this coverage, the elevation angles of the activation and deactivation angles of the beam center at a first target position ahead of the interference-restricted area are different from those of the beam center at a second target position behind the interference-restricted area. Furthermore, within the first interference-restricted area, the satellite beam is controlled so that coverage ahead of the first interference-restricted area is mainly generated by satellites moving toward the first interference-restricted area, and coverage behind the first interference-restricted area is mainly generated by satellites located behind the first interference-restricted area.

[0034] In some embodiments, NTN coverage is configured such that, for example, 80% of the NTN coverage in front of a first interference-restricted area is provided by satellites located in front of the first interference-restricted area, and 20% is provided by satellites located above or behind the first interference-restricted area. The proportions of NTN coverage may vary, but according to the present invention, the proportion provided by satellites in front of the first interference-restricted area exceeds 50%. In some embodiments, NTN coverage is configured such that, for example, 80% of the NTN coverage behind a first interference-restricted area is provided by satellites located behind the first interference-restricted area, and 20% is provided by satellites located above or in front of the first interference-restricted area. The proportions of NTN coverage may vary, but according to the present invention, the proportion provided by satellites behind the first interference-restricted area exceeds 50%.

[0035] The method further includes activating a first communication beam from the satellite toward a first target position when the elevation angle is in the range between an activation angle and a deactivation angle. Here, if the first interference restriction area is located ahead of the satellite's orbital motion, the activation angle is smaller than the deactivation angle. If the first interference restriction area is located behind the satellite's orbital motion, the deactivation angle is smaller than the activation angle. Here, "activating a first communication beam" means initiating or providing a first communication beam from the satellite's antenna toward a first target position.

[0036] As a practical example, consider a satellite moving along an orbit. This satellite has the ability to activate multiple directional communication beams. Typically, the number of these beams is 30, 50, or 100. Each beam is intended to provide communication to its corresponding target location. On the ground, there may be interference-restricted areas where interference from beams (or groups of beams) emitted from the satellite must be eliminated. In practice, this can be achieved by activating or deactivating one communication beam, a set of communication beams, or all communication beams. Activation and deactivation can refer to turning a communication beam on or off. They can also refer to directing an already active beam to a corresponding target location. Furthermore, activation and deactivation can also represent adjusting the transmit power of a communication beam. In some embodiments, at least one communication beam is activated when the elevation angle bypasses the activation angle. In another embodiment, all communication beams are deactivated when the elevation angle bypasses the deactivation angle (i.e., when the elevation angle is greater than the deactivation angle when approaching the target position, and when the elevation angle is smaller than the deactivation angle when the satellite is moving away from the target position).

[0037] The satellite rises above the horizon with respect to the first target position. At this point, the elevation angle between the satellite and the first target position is 0 degrees. The satellite moves along its orbit, and eventually the elevation angle becomes the angle of the first target (i.e., the activation angle) (e.g., 20 degrees). Because the elevation angle is greater than the first target (activation) angle (20 degrees), the first communication beam from the satellite to the first target position is activated. The satellite continues along its orbit, and the elevation angle increases toward the second target (deactivation) angle (e.g., 30 degrees after the target position). Here, 30 degrees (after the target position) refers to the point where the satellite has passed the first target position. At this point, the first communication beam is deactivated. In other words, the first communication beam is activated when the elevation angle is between the activation angle (20 degrees) and the deactivation angle (30 degrees (after the target position angle)). In this example, the first interference restriction zone is located ahead of the satellite's orbital motion, so the activation angle is smaller than the deactivation angle.

[0038] A satellite can form multiple communication beams, such as a second, third, or subsequent beam. Similar logic applies to each communication beam. Activation and deactivation of each communication beam can be controlled by its own activation and deactivation angles. Alternatively, there could be a single communication decision beam that activates each of the other communication beams. In this scenario, activating the first communication beam also activates the others. This reduces complexity by requiring only one pair of control angles per satellite.

[0039] If the interference restriction zone is behind the satellite's orbital motion, the activation logic (of the first communication beam or other communication beams) is modified. For example, the satellite has an elevation angle relative to the first target position. The initial elevation angle is, for example, 80° * (Behind the target position). The communication beam is inactive. The satellite is moving and the elevation angle is 60°. * (Activation angle) exceeds. For example, 59 *The first communication beam is activated. As the satellite moves further in its orbit, the elevation angle changes as a function of movement, as discussed earlier. Eventually, the elevation angle becomes less than 40 degrees. At this angle (the deactivation angle), the first communication beam is deactivated.

[0040] The technological synergy lies in the ability to more precisely control unwanted interference in satellite communications. In fact, it was a surprising finding that when the target position is ahead of or behind the interference restriction zone, the satellite causes more interference compared to the disclosed method when the activation and deactivation angles are the same relative to the target position. The activation (first angle) and deactivation (second angle) angles in this disclosure are determined by the direction of the first interference restriction zone relative to the target position with respect to the satellite's motion. By taking this into consideration, it is possible to implement a satellite communications system that achieves high throughput without causing additional interference.

[0041] In this specification, “communication beam” means a focused beam of electromagnetic waves, such as radio waves or microwaves, that transmit information over a communication link established between a satellite antenna and a target location on Earth. In this specification, “first communication beam” means one of several communication beams transmitted from the satellite antenna toward a first target location. When the first communication beam reaches the first target location, it is received by an antenna associated with that target location. The first target location will decode the signal and process the information contained therein. It will be obvious that the field strength on Earth for the first communication beam is stronger on the side of the first communication beam closer to the satellite than on the side further away from the satellite. A strong field strength is a desirable characteristic for coverage but an undesirable characteristic for interference. In some embodiments, the first communication beam is provided in S-band radio frequencies, i.e., in the range of 1980 MHz to 2010 MHz in the uplink (UL) direction and in the range of 2170 MHz to 2200 MHz in the downlink (DL) direction (band n256). In some embodiments, the first communication beam is provided in the L-band radio frequencies, from 1525 MHz to 1559 MHz for downlink (DL) and from 1626.5 MHz to 1660.5 MHz for uplink (UL) (band n255).

[0042] The activation and deactivation angles are formed by a first communication beam transmitted from the satellite to a specific location on Earth. These angles represent the minimum and maximum angles that the communication beam between the first target location and the satellite can form without causing interference exceeding the limits of the first interference restriction zone. As described above, the activation and deactivation angles depend on the relative position of the target location to the interference restriction zone and the satellite's orbit on Earth.

[0043] Depending on the embodiment, the satellite may activate multiple communication beams for multiple target locations in addition to the first communication beam. The satellite may generate multiple communication beams, such as a second communication beam, a third communication beam, a fourth communication beam, etc., via multiple antennas. Such multiple communication beams may target multiple target locations, such as a second target location, a third target location, a fourth target location, etc. Each of the multiple target locations may receive multiple communication beams from multiple antennas, or it may not. Also, one of the multiple target locations may be associated with a particular communication beam among the multiple communication beams. The multiple communication beams may be on the same or different radio frequency (RF) links as the first communication beam.

[0044] When multiple satellites transmit multiple communication beams toward the same target location (e.g., a first target location), the signals may interfere with each other, potentially causing degradation or interruption of communication. For example, if a satellite transmits a signal on the same frequency and in the same area as a terrestrial 5G / 6G network, interference may occur between the satellite and the 5G / 6G signal, potentially disrupting or blocking radio transmissions of both the satellite and the 5G / 6G network. Advantageously, the method of this disclosure can provide specific target locations around interference-restricted areas, allowing communication beams arriving from the side away from the interference-restricted area to achieve higher coverage and capacity than communication beams arriving from the interference-restricted area side.

[0045] The activation angle and deactivation angle of a non-geostationary satellite system are part of satellite constellation design. When the activation angle and deactivation angle are low, the number of satellites required for the constellation can be less than when the activation angle and deactivation angle are high. When the activation angle is low, the cost of the satellite system decreases. However, when the activation angle and deactivation angle are low, there are also disadvantages such as the inability to avoid buildings and obstacles around the target area, the need for a higher output level, low directivity, and causing interference over a wider range. Furthermore, when the number of satellites in the constellation is small, the total capacity of the satellite communication system decreases.

[0046] According to some embodiments, when there is a first interference limitation area in front of the orbital motion of the satellite, the activation angle is from 20 degrees to 40 degrees, and the deactivation angle is from 60 degrees to 41 * degrees. In this case, the activation angle may be any angle from 20, 25, 30, 35 degrees to any angle from 25, 30, 35, 40 degrees when viewed from the direction approaching the target position. Also, the deactivation angle may be any angle from 60, 65, 70, 75, 80, 85, 90, 85 * 、75 * 、65 * 、55 * 、45 * degrees to any angle from 65, 70, 75, 80, 85, 90, 85 * 、75 * 、65 * 、55 * 、45 * 、41 * degrees. According to some embodiments, when there is a first interference limitation area in front of the orbital motion of the satellite, the activation angle is 25 degrees and the deactivation angle is 80 degrees. According to some embodiments, when there is a first interference limitation area in front of the orbital motion of the satellite, the activation angle is 30 degrees and the deactivation angle is 90 degrees. The notation " * " after the angle refers to the elevation angle of the direction in which the satellite moves away from the target position, and the value of the elevation angle increases from 90 to 0. " *Angles without a notation refer to the elevation angle in the direction in which the satellite approaches the target position, and the elevation angle value increases from 0 towards 90.

[0047] Depending on the embodiment, if there is a first interference limiting area behind the orbital motion of the satellite, the activation angle is 41 to 60 degrees. * Deactivation angle is 40 degrees * From 20 degrees * The angles of activation are 41, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, and 85 degrees. * , 80 * , 75 * , 70 * ,65 * Choose from any of the following degrees: 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 85 * , 80 * , 75 * , 70 * ,65 * , 60 * It may be up to any degree. The deactivation angle is 40 * , 35 * , 30 * ,twenty five * From any of the degrees, 35 * , 30 * ,twenty five * , 20 * It may be up to any of the degrees. In some embodiments, when there is a first interference limiting area behind the orbital motion of the track, the activation angle is 90 degrees and the deactivation angle is 30 degrees. * The angle is 25 degrees. In some embodiments, when there is a first interference limiting area behind the orbital motion of the track, the activation angle is 25 degrees and the deactivation angle is 85 degrees. * It is a degree. The angle after " * The notation " " indicates the elevation angle in the direction the satellite is moving away from the target position, and the elevation angle increases from 90 to 0. * Angles where the notation is not used refer to the direction in which the satellite approaches the target position, that is, the angle in which the elevation angle increases from 0 to 90 degrees. One way to compare the values ​​of these notations is to use the reference value Ref=180-x *Calculate the following, and when the trajectory passes directly above the target position, * This involves comparing any unspecified values ​​with the reference value Ref.

[0048] In some embodiments, the deactivation angle is a function of the interference of multiple communication beams on a first target location, with the deactivation angle decreasing as the interference increases. In some embodiments, the activation angle is a function of the interference of multiple communication beams on a first target location, with the activation angle increasing as the interference increases. As multiple communication beams are activated toward the first target location, the interference at the first target location increases, affecting the signal reception angle at the first target location. The differing phases and amplitudes of the multiple communication beams may merge (or be amplified) or break down at the receiving first target location. As the interference of the multiple beams increases, the beam inclination increases as the satellite moves along its orbit, which increases the activation angle of the first communication beam and decreases the deactivation angle.

[0049] In some embodiments, if the elevation angle is greater than the deactivation angle, the first communication beam is deactivated toward the first target location. After deactivation, the first communication beam is re-radiated toward the second target location. Here, the term “deactivation” relates to the stopping of the first communication beam. Thus, when the elevation angle exceeds the deactivation angle, the first communication beam is focused toward the second target location, which is within the field of view of the satellite orbiting the Earth. When the satellite passes through the first interference restriction zone, it is important to change the target location of the first communication beam so as not to cause interference in the first interference restriction zone. In particular, if the interference restriction zone is large, the first communication beam may be deactivated for a certain period of time so as not to cause harmful interference in the first or second interference restriction zone until the beam target is changed and it is reactivated.

[0050] In some embodiments, the first communication beam is redirected toward a second target position after deactivation, and the redirected first communication beam is activated toward the second target position when its elevation angle is in the range between a new activation angle and a new deactivation angle. Here, if the second interference restriction zone is located ahead of the satellite's orbital motion, the new activation angle is smaller than the new deactivation angle. If the second interference restriction zone is located behind the satellite's orbital motion, the new activation angle is larger than the new deactivation angle. Once the first communication beam is redirected and activated toward a new target position (i.e., a second target position), the elevation angle of the first communication beam at the second target position is between the new activation angle and a new deactivation angle, similar to the elevation angle of the first communication beam at the first target position. Here, the second target position is located behind the first interference restriction zone.

[0051] As stated above, this disclosure also relates to systems and computer program products. The various embodiments and modifications disclosed with respect to the above-described methods will also apply mutatis mutandis to such systems and computer program products.

[0052] In some embodiments, the server system includes at least one server. In particular, at least one server controls the overall operation of the system. In some embodiments, at least one server is implemented as a remote server. In such embodiments, the remote server receives multiple communication beams (i.e., Earth-fixed beams) directed to a fixed target location and limits interference caused by the multiple communication beams (in a defined interference-restricted area). For example, the remote server may be a cloud server providing cloud computing services. In other embodiments, at least one server is implemented as a processor in a computer device. In some embodiments, the server is a single server, and in other embodiments, there are multiple servers. If the system includes a single server, all operations of the system are performed by that single server. If the system includes multiple servers, different operations of the system are performed by different (and specially configured) servers among the multiple servers. For example, a first server among the multiple servers may be configured to identify a first interference-restricted area through which the satellite's orbit passes from a database of restricted areas. A second server among the multiple servers may be configured to activate the first communication beam from the satellite toward the first target location based on the elevation angle of the determined first communication beam.

[0053] The database can be implemented, for example, in the memory of a server system, the memory of a computing device, removable memory, a cloud-based database, or similar forms. Furthermore, by recording restricted areas in the database, the satellite can utilize this information to change the direction of its antenna radiation pattern when passing through these areas.

[0054] The server system is configured to transmit activation angle and deactivation angle values ​​to the satellite via a communication network between the first target location and the satellite. The communication network includes a medium (e.g., a communication channel) for the satellite and the first target location to communicate with each other. The communication network may be a wired or wireless communication network. Examples of communication means / networks include, but are not limited to, the Internet, Local Area Networks (LANs), Wireless Personal Area Networks (WPANs), Wireless Local Area Networks (WLANs), Wireless Wide Area Networks (WWANs), Cloud Networks, Long-Term Evolution (LTE) networks, Plain Old Telephone Services (POTS), Metropolitan Area Networks (MANs), and / or the Internet.

[0055] In some embodiments, the satellite includes an antenna for providing a first communication beam from the satellite.

[0056] In some embodiments, the first communication beam is maintained pointed toward the first target position by adjusting the direction of the antenna's radiation pattern according to its trajectory.

[0057] Depending on the embodiment, the satellite may activate multiple communication beams for multiple target locations in addition to the first communication beam.

[0058] Depending on the embodiment, if there is a first interference limiting zone ahead of the satellite's orbital motion, the activation angle is 20 to 40 degrees and the deactivation angle is 60 to 41 degrees. * It becomes a degree.

[0059] Depending on the embodiment, if there is a first interference limiting area behind the orbital motion of the satellite, the activation angle is 41 to 60 degrees. * Deactivation angle is 40 degrees * From 20 degrees * It becomes a degree.

[0060] In some embodiments, the deactivation angle is a function of interference to the first target position by multiple communication beams, and as the interference increases, the angular difference between the activation angle and the deactivation angle decreases.

[0061] In some embodiments, the activation angle is a function of interference to the first target position by multiple communication beams, and as the interference increases, the angular difference between the activation angle and the deactivation angle decreases.

[0062] In some embodiments, if the elevation angle is greater than the deactivation angle, the first communication beam toward the first target position is deactivated, and after deactivation, the first communication beam is redirected toward the second target position.

[0063] In some embodiments, the first communication beam is redirected toward a second target position after deactivation, and the redirected first communication beam is activated toward the second target position when the elevation angle is in the range between the new activation angle and the new deactivation angle.

[0064] Here, if the second interference restriction zone is located ahead of the satellite's orbital motion, the new activation angle is smaller than the new deactivation angle.

[0065] Furthermore, if the second interference restriction zone is located behind the satellite's orbital motion, the new deactivation angle is smaller than the new activation angle.

[0066] Here is another example of the logic for forming communication beam control signals.

[0067] Table 1: When the interference restriction zone is ahead of the satellite's direction of motion, and the first target position is ahead of the interference restriction zone relative to the satellite's direction of motion (EA = elevation angle, d1 = activation angle, d2 = deactivation angle) TIFF2026509111000002.tif64170

[0068] Table 1 shows an example of a satellite with three beams (beams 1, 2, and 3). In this example, all beams become inactive when the elevation angle is less than the activation angle d1, and all beams become inactive when the elevation angle exceeds the deactivation angle d2. Beam 2 becomes inactive when the elevation angle exceeds d3 (the deactivation angle for beam 2). The remaining beams remain active. When the angle exceeds d2, all beams become inactive.

[0069] Table 2: Interference restriction area in front of the beam center TIFF2026509111000003.tif72170

[0070] Table 2 shows an example where beams 1 and 2 are activated at activation angle d1. Beam 3 has a separate activation angle d4 > d1. When the angle is between d1 and d4, only beam 3 is deactivated. When the angle is between d4 and d2, all beams are activated, and when the angle exceeds d2, all beams are deactivated.

[0071] [Detailed explanation of the drawing]

[0072] Referring to Figure 1, a flowchart is shown illustrating the steps of a method for controlling satellite communications of a satellite flying in orbit above the Earth, according to an embodiment of the present invention. In step 102, a first target position is provided on the Earth's surface. In step 104, the satellite's orbit above the Earth is determined. In step 106, a first interference restriction zone is identified through which the satellite's orbit passes. In step 108, the elevation angle between the satellite and the first target position is determined. This elevation angle is the angle between the Earth's horizontal plane and a vector pointing from the first target position to the satellite in orbit at a given moment. In step 110, a first communications beam is activated from the satellite towards the first target position when the elevation angle is within the range between an activation angle and a deactivation angle. Here, if the first interference restriction zone is located ahead of the satellite's motion along its orbit, the activation angle is smaller than the deactivation angle. Conversely, if the first interference restriction zone is located behind the satellite's motion along its orbit, the activation angle is larger than the deactivation angle.

[0073] Steps 102, 104, 106, 108, and 110 are merely illustrative, and other options may be provided. That is, one or more steps may be added, one or more steps may be omitted, or one or more steps may be performed in a different order without departing from the scope of the appended claims.

[0074] Referring to Figures 2A and 2B, block diagrams of the architecture of a system 200 for controlling satellite communications of a satellite 202 flying along an orbit 204 above the Earth 206 are shown according to an embodiment of the present invention. The system 200 comprises a server system configured to perform the operation of the system. As shown in Figures 2A and 2B, the satellite 202 is flying along an orbit 204 above the Earth 206. While flying along the orbit 204, the satellite 202 takes on various positions P1, P2, P3, P4, and P5, from which the satellite 202 activates a first communication beam 208 toward a first target position 210 and a second target position 212. The server system is configured to identify the first target position 210 and the second target position 212 on the surface of the Earth 206, determine the orbit 204 of the satellite 202 above the Earth 206, and identify a first interference restriction area 214 (see Figure 2B) through which the satellite orbit 204 passes, from a database of restricted areas. The system includes a server system configured to determine the orbit 204 of satellite 202 above Earth 206. Furthermore, the server system is configured to determine the elevation angles (e.g., δ1, δ2, δ3, δ3) of satellite 202 with respect to a first target position 210 or a second target position 212. Here, the elevation angle is the angle between the horizontal plane of Earth 206 and a vector pointing from the first target position 210 or the second target position 212 to satellite 202 in orbit 204 at a given moment. Furthermore, the server system is configured to activate a first communication beam 208 from satellite 202 toward the first target position 210 or the second target position 212 when the elevation angles are within the range of activation angles δ1, δ3 and deactivation angles δ2, δ4. Here, if the first interference restriction zone 214 is located ahead of the satellite 202 in the direction of motion along its orbit 204, the activation angles δ1 and δ3 are smaller than the deactivation angles δ2 and δ4. Also, if the first interference restriction zone 214 is located behind the satellite 202 in the direction of motion along its orbit 204, the activation angle δ1 is larger than the deactivation angle δ2. The server system is configured to transmit the values ​​of the activation angle δ1 and the deactivation angle δ2 to the satellite 202.

[0075] As shown in the figure, when the first interference restriction area 214 is forward relative to the motion of satellite 202 along its orbit 204, the activation angle δ1 is smaller than the deactivation angle δ2. When the first interference restriction area 214 is backward relative to the motion of satellite 202 along its orbit 204, the deactivation angle δ4 is smaller than the activation angle δ1. Here, when satellite 202 is rising above the horizon, the angle is 0 degrees. When satellite 202 is directly above the first target position (nadir) 210, the elevation angle increases to 90 degrees, and as satellite 202 moves along its orbit 204, the elevation angle increases to 90 degrees. * From 0 degrees * Decreases to degrees. (Symbol) * This indicates that the target position is behind the orbit.

[0076] The first communication beam 208 from satellite 202 is activated and directed toward the first target position 210 when satellite 202 is between positions P1 and P3 and its elevation angle is between activation angle δ1 and deactivation angle δ2. The first communication beam 208 from satellite 202 is activated and directed toward the second target position 212 when satellite 202 is between positions P3 and P5 and its elevation angle is between activation angle δ3 and deactivation angle.

[0077] As shown in the figure, the first communication beam 208 causes interference and noise in the surrounding area 210A of the first target area 210 and the surrounding area 212A of the second target area 212, respectively. When satellite 202 moves to position P3, the direction of the first communication beam 208 is changed from the first target position 210 to the second target position 212. In this way, satellite 202 can provide communications while orbiting the Earth 206.

[0078] As shown in Figure 2B, when satellite 202 is at position P3.1, the first communication beam 208 from satellite 202 is deactivated and not directed toward the first target position 210. Similarly, when satellite 202 is at position P2.1, the first communication beam 208 emitted from satellite 202 is deactivated and not directed toward the first target position 212. This is because the first target position 210 and the first target position 212 are not within the satellite 202's line of sight at their respective positions.

[0079] Those skilled in the art will understand that Figure 2 shows a simplified architecture of System 200 for clarity and does not unduly limit the scope of the claims herein. Specific embodiments of System 200 are provided as examples and should not be construed as limiting to a specific number or type of server systems, satellites, and target locations. Those skilled in the art will recognize many variations, alternatives, and modifications of the embodiments of this disclosure.

[0080] Referring to Figures 3A-C, an example of the motion of satellite 202 and how the surrounding region changes its shape factor as satellite 202 moves are shown according to an embodiment of the present invention. As shown in Figure 3A, satellite 202 is at position P1, and the first target position 210 is receiving the first communication beam 208 from satellite 202. Satellite 202 and the first target position 210 form an elevation angle δ1. At this position, a surrounding region 210A is also shown around the first target position 210, which experiences more interference on its right side. As shown in Figure 3B, satellite 202 moves from position P1 to position P2, and at this position, the surrounding region 210A of the first target position 210 experiences equal interference on its right and left sides. As shown in Figure 3C, satellite 202 moves to position P3. As satellite 202 moves from position P1 to P3, the elevation angle between satellite 202 and the first target position 210 changes from δ1 to δ2. Furthermore, at this position, the area 210A surrounding the first target position 210 is subjected to more interference on its left side. During operation, the first communication beam 208 is active when its elevation angle is between δ1 and δ2. It is inactive outside this range.

[0081] Referring to Figures 4A-E, the step-by-step operation of a satellite 202 flying along an orbit 204 above the Earth 206 is shown according to an embodiment of the present invention. As shown in Figures 4A and 4B, in steps S1 and S2, the satellite 202 moves along the orbit 204 from position P1 to P2. The first communication beam 208, directed to a first target position 210, changes its elevation angle from an activation angle δ1 to a deactivation angle δ2 as it moves from position P1 to P2. The first communication beam 208 is activated when its elevation angle exceeds the activation angle δ1. The first communication beam 208 remains activated until point P2 where its elevation angle becomes the deactivation angle δ2. As shown in Figure 4C, in step S3, the first communication beam 208 is deactivated at position P3 where its elevation angle is greater than or equal to the deactivation angle δ2. In other words, it is deactivated when the orbit 204 of satellite 202 passes through the first interference restriction zone 214. As shown in Figures 4D and 4E, through steps S4 and S5, satellite 202 moves along orbit 204 from position P4 to P5. The first communication beam 208, directed to the second target position 210, changes its elevation angle from an activation angle δ3 to a deactivation angle δ4 as it moves from position P4 to P5. Here, since the first interference restriction zone 214 is behind the direction of movement of satellite 202, the activation angle δ3 is greater than the deactivation angle δ4.

[0082] Referring to Figures 5A-C, step-by-step operation of a satellite 202 flying along orbit 204 above Earth 206 is shown according to an embodiment of the present invention. As shown in the figure, satellite 202 activates multiple communication beams toward each target position 210 (marked "x"). The first communication beam is transmitted toward target position 210 (marked "A1"). Here, the first interference restriction zone 214 is shown as an ellipse. No target zone shall generate radio noise exceeding the regulatory level toward the first interference restriction zone 214. As shown in the figure, the second target position 212 (marked B1) is located on the opposite side of the first interference restriction zone 214.

[0083] As shown in Figure 5A, multiple communication beams become active as satellite 202 approaches the first interference restriction zone 214. As shown in Figure 5B, satellite 202 is located above the first interference restriction zone 214. As shown in the figure, a portion of the location area of ​​the multiple communication beams is still active. As shown in Figure 5C, satellite 202 redirects the first communication beam 208 from the first target location A1 to the second target location B1, and a portion of the multiple communication beams remains active in this step. It can be seen that satellite 202 can maintain good communication coverage using the provided communication beam control logic.

[0084] Referring to Figure 6, a radiation pattern 600 of a satellite communication beam on Earth according to an embodiment of the present invention is shown. As shown in the figure, the satellite beam on Earth has a radiation pattern (shown by a dashed line) that depends on the antenna inside the satellite. As shown in the figure, the vertical axis is latitude, the horizontal axis is longitude, and the antenna gain is shown in decibels by a hatch pattern. Here, the position of the satellite is shown by ×, and the center of the satellite beam is shown by ●.

[0085] Referring to Figure 7, an antenna model geometry 700 according to an embodiment of the present invention is shown. As shown in the figure, a plurality of antenna centers, each separated by a distance d, are configured to radiate a communication beam toward a predetermined target position.

[0086] Referring to Figures 8A and 8B, a shared satellite communication scenario 800 between user equipment on a non-terrestrial network (NTN) 802 and a terrestrial network (TN) 804 is shown according to an embodiment of the present invention. As shown in the figures, the area (map) is covered by multiple satellite beams. Figure 8A shows a satellite located in the lower left corner of the map, and Figure 8B shows a satellite located in the upper right corner of the map. The movement of the satellites is from the lower left to the upper right corner of the figure. The system optimizes the beams so that the total interference of the beams does not exceed a set limit. (Here, the interference-to-noise ratio at the TN user equipment (UE) receiver is <0 dB.) Active beams are marked with ○, and inactive beams are marked with ×.

[0087] Referring to Figure 9, a world map 900 is shown illustrating some of the regions of the S-band ITU-R frequency allocation according to embodiments of this disclosure. As shown in the figure, the Radio Rules of the International Telecommunication Union Radio Sector (ITU-R) classify the world into different regions: Region 1 (Europe, the Middle East, and Africa (EMEA)), Region 2 (the Americas and the Caribbean), and Region 3 (Asia and Oceania).

[0088] It is possible to modify the embodiments of this disclosure described above without departing from the scope defined by the attached claims. Expressions such as “includes,” “equip,” “incorporates,” “possesses,” and “is” used to describe and claim this disclosure are intended to be interpreted non-exclusively, that is, to allow for the existence of items, parts, or components not expressly described. The absence of explicit indication that an element is plural does not preclude the existence of multiple such elements.

Claims

1. A method for controlling satellite communications of a satellite orbiting the Earth, To provide a first target location on the Earth's surface; To determine the orbit of the aforementioned satellite above the Earth; Identifying a first interference restriction zone through which the orbit of the aforementioned satellite passes; Determining the elevation angle between the satellite and the first target position, wherein the elevation angle is the angle between the horizontal plane of the Earth and a vector pointing from the first target position to the satellite in orbit at a given moment; When the elevation angle is within the range between the activation angle and the deactivation angle, the first communication beam is activated from the satellite toward the first target position; This includes, however, If the first interference restriction zone is located ahead of the motion of the satellite along the orbit, the activation angle is smaller than the deactivation angle. If the first interference restriction zone is located behind the motion of the satellite along the orbit, the deactivation angle is smaller than the activation angle; The method further includes deactivating the first communication beam when the elevation angle exceeds the deactivation angle; Methods that include...

2. The method according to claim 1, wherein the first communication beam is maintained directed toward the first target position by adjusting the direction of the antenna's radiation pattern according to the trajectory.

3. The satellite is capable of activating multiple communication beams for each of multiple target locations, in addition to the first communication beam. When the elevation angle exceeds the deactivation angle, the first communication beam and all of the plurality of communication beams are deactivated. The method according to claim 1 or 2.

4. If the first interference limiting zone is located ahead of the orbital motion of the satellite, the activation angle is 20 to 40 degrees, and the deactivation angle is 60 to 41 degrees. ＊ The method according to any one of claims 1 to 3, wherein the degree is

5. If the first interference limiting area is located behind the orbital motion of the satellite, the activation angle is 41 to 60 degrees. ＊ The deactivation angle is 40 degrees. ＊ From 20 degrees ＊ The method according to any one of claims 1 to 3, wherein the degree is

6. The method according to claim 3 or 4, wherein the deactivation angle is a function of the interference of the plurality of communication beams to the first target position, and the angular difference between the activation angle and the deactivation angle decreases as the interference increases.

7. The method according to claim 3 or 5, wherein the activation angle is a function of the interference of the plurality of communication beams on the first target position, and the angular difference between the activation angle and the deactivation angle decreases as the interference increases.

8. The method according to any one of claims 1 to 7, wherein if the elevation angle is greater than the deactivation angle, the first communication beam toward the first target position is deactivated, and after deactivation, the first communication beam is redirected toward the second target position.

9. The method according to claim 8, wherein the first communication beam is deactivated and then redirected toward the second target position, and the redirected first communication beam is activated toward the second target position when the elevation angle is in the range between a new activation angle and a new deactivation angle, provided that, If the second interference restriction zone is located ahead of the satellite's orbital motion, the new activation angle is smaller than the new deactivation angle. If the second interference restriction zone is located behind the satellite's orbital motion, the new deactivation angle is smaller than the new activation angle. method.

10. A system for controlling satellite communications of a satellite orbiting the Earth, wherein the system comprises a server system, and the server system is - Identify the first target location on the Earth's surface; - Determine the orbit of the satellite above the Earth; - Identify a first interference restriction area through which the satellite's orbit passes from the restricted area database; - Determining the elevation angle between the satellite and the first target position, wherein the elevation angle is the angle between the horizontal plane of the Earth and the vector pointing from the first target position to the satellite in orbit at a given moment; - When the elevation angle is within the range between the activation angle and the deactivation angle, activate the first communication beam from the satellite toward the first target position; It is configured in such a way, however, - If the first interference restriction zone is located ahead of the motion of the satellite along the orbit, the activation angle is smaller than the deactivation angle. - If the first interference restriction zone is located behind the motion of the satellite along the orbit, the deactivation angle is smaller than the activation angle; The server system is further configured to transmit the activation angle value and the deactivation angle value to the satellite; system.

11. The system according to claim 10, wherein the satellite comprises an antenna for providing the first communication beam from the satellite.

12. The system according to claim 10 or 11, wherein the first communication beam is maintained directed toward the first target position by adjusting the direction of the antenna's radiation pattern according to the trajectory.

13. The satellite is capable of activating multiple communication beams for each of multiple target locations, in addition to the first communication beam. When the elevation angle exceeds the deactivation angle, the first communication beam and each of the plurality of communication beams are deactivated. The system according to any one of claims 10 to 12.

14. If there is a first interference restriction zone ahead of the orbital motion of the satellite, the activation angle is 20 to 40 degrees, and the deactivation angle is 60 to 41 degrees. ＊ The system according to any one of claims 10 to 13, wherein the degree is

15. If the first interference limiting area is located behind the orbital motion of the satellite, the activation angle is 41 to 60 degrees. ＊ The deactivation angle is 40 degrees. ＊ From 20 degrees ＊ The system according to any one of claims 10 to 13, wherein the degree is

16. The system according to claim 13 or 14, wherein the deactivation angle is a function of the interference of the plurality of communication beams to the first target position, and the angular difference between the activation angle and the deactivation angle decreases as the interference increases.

17. The system according to claim 13 or 15, wherein the activation angle is a function of the interference of the plurality of communication beams to the first target position, and the angular difference between the activation angle and the deactivation angle decreases as the interference increases.

18. The system according to any one of claims 10 to 17, wherein if the elevation angle is greater than the deactivation angle, the first communication beam toward the first target position is deactivated, and after deactivation, the first communication beam is redirected toward the second target position.

19. The system according to claim 18, wherein the first communication beam is deactivated and then redirected toward the second target position, and the redirected first communication beam is activated toward the second target position when the elevation angle is in the range between a new activation angle and a new deactivation angle, provided that, If the second interference restriction zone is located ahead of the satellite's orbital motion, the new activation angle is smaller than the new deactivation angle. If the second interference restriction zone is located behind the satellite's orbital motion, the new deactivation angle is smaller than the new activation angle. system.

20. A computer program product comprising program instructions stored in a non-volatile machine-readable data storage medium, wherein, when executed by a processor, the program instructions cause the processor to perform a step according to any one of claims 10 to 19.

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