Information processing device, program, information processing system, and information processing method

Abstract

To provide an information processing device, an information processing system, an information processing method, and a program that can effectively relieve a disaster-stricken area using an aircraft.SOLUTION: An information processing device 200 includes a storage unit 202 that stores SL antenna performance information of an SL antenna, which is a collinear antenna, and aircraft performance information of an aircraft equipped with an SL antenna such that horizontal polarization is omnidirectional, an acquisition unit 204 that acquires information on the coverage area of the wireless communication service provided by the aircraft, a simulation unit 206 that simulates the SL wireless communication area formed by the SL beam irradiated by the SL antenna while the aircraft is flying in a circle, on the basis of the SL antenna performance information and the aircraft performance information, and a determination unit 208 that determines the trajectory of the aircraft such that the coverage area is included in the SL wireless communication area while the aircraft is flying in a circle, on the basis of the information on the coverage area of the wireless communication service and the results of simulating the SL wireless communication area.SELECTED DRAWING: Figure 14

Description

[Technical Field]

[0001] The present invention relates to an information processing device, a program, an information processing system, and an information processing method. [Background technology]

[0002] Patent Document 1 describes an unmanned aerial vehicle having a base station function for a wireless communication network. [Prior art document] [Patent documents] [Patent Document 1] JP 2023-105204 A Summary of the Invention [Means for solving the problem]

[0003] According to one embodiment of the present invention, an information processing device is provided. The information processing device may include a storage unit that stores SL antenna performance information indicating the performance of an SL (Service Link) antenna, which is a collinear antenna, and aircraft performance information indicating the performance of an aircraft equipped with the SL antenna so that horizontal polarization is omnidirectional. The information processing device may include an acquisition unit that acquires service area information indicating a service area for a wireless communication service provided by the aircraft. The information processing device may include a simulation unit that simulates an SL wireless communication area formed by an SL beam irradiated by the SL antenna while the aircraft is flying in a circular flight, based on the service area information and the aircraft performance information. The information processing device may include a determination unit that determines the trajectory of the aircraft while the aircraft is flying in a circular flight, based on the service area information and a simulation result of the SL wireless communication area simulated by the simulation unit, so that the service area is included in the SL wireless communication area.

[0004] In the information processing device, the simulation unit may simulate the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit, and the determination unit may determine the position of the center of the circular orbit of the aircraft so that the target area is included in the SL wireless communication area while the aircraft is flying in a circular orbit.

[0005] In any of the information processing devices, the storage unit may store the SL antenna performance information including SL antenna gain information indicating the antenna gain of the SL antenna, and the simulation unit may simulate the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit by deriving inner and outer diameters of the footprint of the SL wireless communication area based on the SL antenna gain information.

[0006] In any of the information processing devices, the simulation unit may simulate the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit when the flight altitude of the aircraft is each of a plurality of flight altitudes, and the determination unit may determine the flight altitude of the aircraft so that the target area to be provided is included in the SL wireless communication area while the aircraft is flying in a circular orbit.

[0007] In any of the information processing devices, the storage unit may store the aircraft performance information including minimum flight speed information indicating the minimum flight speed of the aircraft when it is flying in a circle, and permissible bank angle information indicating the permissible bank angle of the aircraft when it is flying in a circle, and the simulation unit may simulate the SL wireless communication area formed by the SL beam while the aircraft is flying in a circle when the flight speed of the aircraft is each of a plurality of flight speeds that are equal to or greater than the minimum flight speed indicated by the minimum flight speed information, by deriving the radius of the circular orbit of the aircraft when the bank angle of the aircraft is smaller than the permissible bank angle indicated by the permissible bank angle information, and the determination unit may determine the flight speed of the aircraft and the radius of the circular orbit of the aircraft so that the provision target region is included in the SL wireless communication area while the aircraft is flying in a circle.

[0008] In any of the information processing devices, the acquisition unit may acquire the provision target area information indicating the provision target areas at two different locations, and the determination unit may determine the trajectory of the aircraft so that the two provision target areas at different locations are included in the SL wireless communication area while the aircraft is flying in a circle.

[0009] In any of the information processing devices, the storage unit may further store FL antenna performance information indicating the performance of an FL (Feeder Link) antenna, which is a collinear antenna, and installation location information indicating the installation location of a gateway installed on the ground, and the simulation unit may further simulate, based on the FL antenna performance information and the aircraft performance information, an FL wireless communication area formed by the FL beam irradiated by the FL antenna while the aircraft equipped with the FL antenna is flying in a circle so that the horizontal polarization is omnidirectional, and the determination unit may determine the trajectory of the aircraft, based further on the installation location information and the simulation results of the simulation unit simulating the FL wireless communication area, so that the target area to be provided is included in the SL wireless communication area and the installation location of the gateway is included in the FL wireless communication area while the aircraft is flying in a circle.

[0010] Any of the information processing devices may further include a control unit that controls the flying object so that the flying object flies in a circle along the trajectory determined by the determination unit.

[0011] In any of the information processing devices, the acquisition unit may acquire the provision target area information indicating the provision target area that is a disaster-affected area that has been affected by a disaster.

[0012] According to one embodiment of the present invention, there is provided a program that, when executed by a computer, causes the computer to function as any one of the information processing devices.

[0013] According to one embodiment of the present invention, there is provided an information processing system. The information processing system may include any one of the information processing devices described above. The information processing system may include the flying object.

[0014] According to one embodiment of the present invention, there is provided an information processing method executed by a computer. The information processing method may include an acquisition step of acquiring service area information indicating a service area of ​​a wireless communication service provided by an aircraft equipped with an SL antenna, which is a collinear antenna, so that the horizontally polarized waves of the SL antenna are omnidirectional. The information processing method may include a simulation step of simulating an SL wireless communication area formed by an SL beam emitted by the SL antenna while the aircraft is flying in a circle, based on SL antenna performance information indicating the performance of the SL antenna and aircraft performance information indicating the performance of the aircraft, both stored in the computer. The information processing method may include a determination step of determining the trajectory of the aircraft while the aircraft is flying in a circle, based on the service area information and a simulation result of simulating the SL wireless communication area in the simulation step, so that the service area is included in the SL wireless communication area.

[0015] The above summary of the invention does not list all of the necessary features of the present invention, and subcombinations of these features may also constitute inventions. [Brief explanation of the drawings]

[0016] [Figure 1] An example of a system 10 is shown schematically. [Figure 2] 1 is an explanatory diagram for explaining an example of the performance of an antenna mounted on the aircraft 100. FIG. [Figure 3] 1 is an explanatory diagram for explaining an example of a method for mounting an antenna on an aircraft 100. FIG. [Figure 4] 1 is an explanatory diagram for explaining an example of the relationship between the mounting method of an antenna on an aircraft 100 and the footprint. [Figure 5] 1 is an explanatory diagram illustrating an example of a turning flight trajectory of the flying body 100. FIG. [Figure 6]This is an explanatory diagram for explaining an example of aircraft performance information for the aircraft 100, recommended conditions for the aircraft 100 when conducting a demonstration experiment, and the relationship between the flight speed of the aircraft 100, the radius of the circular orbit, and the bank angle. [Figure 7] FIG. 10 is an explanatory diagram illustrating an example of a link budget condition. [Figure 8] 2 is an explanatory diagram for explaining an example of the relationship between the flight altitude of the flying body 100 and the footprint. FIG. [Figure 9] 1 is an explanatory diagram illustrating an example of the relationship between the footprint and the radius of the circular orbit of the flying body 100. FIG. [Figure 10] 10A and 10B are explanatory diagrams illustrating an example of a simulation result of a link budget of a feeder link and an FL wireless communication area. [Figure 11] 10A and 10B are explanatory diagrams illustrating an example of a simulation result of a link budget of a service link and an SL wireless communication area. [Figure 12] 1 is an explanatory diagram for explaining an example of the relationship between the flight altitude and the radius of the circular orbit of the flying body 100 and the footprint. [Figure 13] 10 is an explanatory diagram for explaining an example of a decision made by the information processing device 200. FIG. [Figure 14] 2 shows an example of a functional configuration of an information processing device 200. [Figure 15] FIG. 2 is an explanatory diagram for explaining an example of a processing flow of the system 10. [Figure 16] An example of the hardware configuration of a computer 1200 that functions as the information processing device 200 is shown in schematic form. DETAILED DESCRIPTION OF THE INVENTION

[0017] When an omnidirectional VH-polarized dual-mode collinear antenna, a typical balloon-based communication antenna, is mounted on an aircraft such as a high-speed UAV (Unmanned Aerial Vehicle), the constant coverage area, which is the area that is always included in the wireless communication area formed by the mounted antenna, is limited depending on the antenna characteristics of the antenna mounted on the aircraft (antennas mounted on aircraft are sometimes referred to as "mounted antennas") and the aircraft's flight route. In this embodiment, the system simulates the constant coverage area based on, for example, the antenna characteristics of the mounted antenna, the mounting method for the mounted antenna on the aircraft, the aircraft's flight characteristics such as turning performance and flight speed, and the aircraft's flight route such as flight altitude and turning radius. Based on the results of the simulation of the constant coverage area, the system calculates the aircraft's flight route to establish an optimal wireless communication area in a disaster-stricken area, and autonomously flies the aircraft along the calculated flight route. This allows the aircraft to effectively rescue the disaster-stricken area.

[0018] The present invention will be described below through embodiments of the invention, but the following embodiments do not limit the invention according to the claims. Furthermore, not all of the combinations of features described in the embodiments are necessarily essential to the solution of the invention.

[0019] 1 schematically illustrates an example of a system 10. The system 10 may include an air vehicle 100 and an information processing device 200. The system 10 may further include a disaster information management device 400. The system 10 may be an example of an information processing system.

[0020] The air vehicle 100 may be any air vehicle capable of providing wireless communication services. The air vehicle 100 may be, for example, an unmanned aerial vehicle. The air vehicle 100 may be, for example, a drone. The air vehicle 100 may be, for example, an MQ-9B SeaGuardian (registered trademark) manufactured by General Atomics Aeronautical Systems. The air vehicle 100 may also be a manned aircraft.

[0021] The flying vehicle 100 is equipped with an SL antenna 120 and an FL antenna 140. The SL antenna 120 is, for example, a collinear antenna. The FL antenna 140 is, for example, a collinear antenna. The collinear antennas used as the SL antenna 120 and the FL antenna 140 may be antennas mounted on a balloon-borne base station. Details of the performance of the antennas mounted on the flying vehicle 100 and the method of mounting the antennas on the flying vehicle 100 will be described later.

[0022] The aircraft 100 forms an SL wireless communication area 122 by, for example, irradiating an SL beam using the SL antenna 120, and provides wireless communication services to the communication terminal 300 within the SL wireless communication area 122. The aircraft 100 establishes a service link between the aircraft 100 and the communication terminal 300 within the SL wireless communication area 122 using, for example, the SL antenna 120.

[0023] The communication terminal 300 may be any communication terminal capable of establishing a service link with the air vehicle 100. For example, the communication terminal 300 may be a mobile phone such as a smartphone, a tablet terminal, a wearable terminal, or the like. The communication terminal 300 may be a PC (Personal Computer). The communication terminal 300 may be an IoT (Internet of Things) terminal. The communication terminal 300 may include anything that falls under the IoE (Internet of Everything) category.

[0024] The air vehicle 100 establishes a feeder link between the ground-based gateway 40 and the air vehicle 100, for example, by emitting an FL beam using the FL antenna 140. The air vehicle 100 may access the network 20 via the gateway 40.

[0025] The network 20 may include a core network provided by a telecommunications carrier. The core network may conform to, for example, a 5G (5th Generation) communication system. The core network may conform to a 6G (6th Generation) communication system or later mobile communication system. The core network may conform to a 3G (3rd Generation) communication system. The core network may conform to an LTE (Long Term Evolution) communication system. The network 20 may include the Internet.

[0026] The aircraft 100 communicates, for example, based on a communication control signal that controls the communication function of the aircraft 100. The aircraft 100 communicates, for example, based on a communication control signal received from an external device. The aircraft 100 may generate a communication control signal and communicate based on the generated communication control signal.

[0027] The aircraft 100, for example, forms an SL wireless communication area 122 in the service area 60 while circling above the service area 60 for the wireless communication service provided by the aircraft 100. Details of the circling flight of the aircraft 100 will be described later.

[0028] The air vehicle 100 flies, for example, based on a flight control signal that controls the flight functions of the air vehicle 100. The air vehicle 100 flies, for example, based on a flight control signal received from an external device. The air vehicle 100 may generate a flight control signal and fly based on the generated flight control signal. In this case, the air vehicle 100 may be an autonomous air vehicle that flies autonomously.

[0029] The information processing device 200 executes various information processing operations. For example, the information processing device 200 executes a determination process for determining the trajectory of the flying object 100.

[0030] The information processing device 200 determines the trajectory of the aircraft 100 based on, for example, provision target area information indicating the provision target area 60, SL antenna performance information indicating the performance of the SL antenna 120, and aircraft performance information indicating the performance of the aircraft 100. For example, the information processing device 200 simulates an SL wireless communication area 122 formed by an SL beam irradiated by the SL antenna 120 while the aircraft 100 is flying in a circle, based on the SL antenna performance information and the aircraft performance information. Thereafter, the information processing device 200 determines the trajectory of the aircraft 100 based on the provision target area information and a simulation result of the SL wireless communication area 122, such that the provision target area 60 is included in the SL wireless communication area 122 while the aircraft is flying in a circle. Details of the information processing device 200 simulating the SL wireless communication area 122 will be described later.

[0031] The information processing device 200 determines the trajectory of the flying object 100, for example, further based on FL antenna performance information indicating the performance of the FL antenna 140 and installation location information indicating the installation location of the gateway 40. For example, the information processing device 200 simulates an FL wireless communication area formed by the FL beam irradiated by the FL antenna 140 while the flying object 100 is flying in a circular motion, based on the FL antenna performance information and the flying object performance information. Thereafter, the information processing device 200 determines the trajectory of the flying object 100, further based on the installation location information and the simulation result of the simulating the FL wireless communication area, so that the service target region 60 is included in the SL wireless communication area 122 and the installation location of the gateway 40 is included in the FL wireless communication area while the flying object 100 is flying in a circular motion. Details of the information processing device 200 simulating the FL wireless communication area will be described later.

[0032] The information processing device 200 is installed, for example, on the ground. The information processing device 200 may be mounted on the flying object 100. In this case, the information processing device 200 and the flying object 100 may be one device, or the information processing device 200 and the flying object 100 may be two different devices.

[0033] The disaster information management device 400 manages disaster information related to disasters that have occurred. The disaster may be, for example, an earthquake. The disaster may be, for example, a tsunami. The disaster may be, for example, a typhoon. The disaster may be, for example, a flood. The disaster may be, for example, a high tide. The disaster may be, for example, heavy rain. The disaster may be, for example, heavy snow. The disaster may be, for example, a landslide. The disaster may be, for example, a volcanic eruption. The disaster may be any other natural disaster. The disaster may be a man-made disaster such as a fire.

[0034] The disaster information may include, for example, disaster area information indicating an area affected by a disaster. The disaster area may be an example of the provision target area 60.

[0035] The disaster information includes, for example, disaster type information indicating the type of disaster, disaster scale information indicating the scale of the disaster, and any other information related to the disaster that has occurred.

[0036] The information processing device 200 receives disaster information from, for example, the disaster information management device 400 via the network 20. The information processing device 200 may perform various information processes based on the received disaster information. The disaster information may be an example of provision target area information.

[0037] 2 is an explanatory diagram for explaining an example of the performance of the antennas mounted on the aircraft 100. Here, an example of the performance of the FL antenna 140 and an example of the performance of the SL antenna 120 will be explained.

[0038] The upper diagram of Fig. 2 is an explanatory diagram for explaining an example of the FL antenna performance information and the SL antenna performance information. The FL antenna performance information and the SL antenna performance information shown in the upper diagram of Fig. 2 are as follows.

[0039] The frequency band of the FL antenna 140 is "3305 to 3325 MHz, 3375 to 3395 MHz (3.3 GHz band)." The antenna power of the FL antenna 140 is "1 W (30 dBm)." The antenna gain of the FL antenna 140 is "6 dBi or more." The antenna type of the FL antenna 140 is a "VH polarized dual-mode collinear antenna." The horizontal half-width of the FL antenna 140 is "omnidirectional." The vertical half-width of the FL antenna 140 is "approximately 19°." Note that the horizontal half-width and vertical half-width are values ​​when the antenna is perpendicular to the horizontal plane.

[0040] The frequency band of the SL antenna 120 is "1960 to 1980 MHz, 2150 to 2170 MHz (2 GHz band)". The antenna power of the SL antenna 120 is "10 W (40 dBm)" at "5 W x 2 waves". The antenna gain of the SL antenna 120 is "6 dBi or more". The antenna type of the SL antenna 120 is a "VH polarized dual-mode collinear antenna". The horizontal plane half width of the SL antenna 120 is "omnidirectional". The vertical plane half width of the SL antenna 120 is "approximately 19°".

[0041] 2 is an explanatory diagram illustrating an example of the antenna pattern of the FL antenna 140. When the FL antenna 140 is perpendicular to the horizontal plane, the horizontally polarized waves of the FL antenna 140 are omnidirectional, as shown by the graph of the horizontally polarized waves of the FL antenna 140, and the vertically polarized waves of the FL antenna 140 have directionality, as shown by the graph of the vertically polarized waves of the FL antenna 140.

[0042] 2 is an explanatory diagram illustrating an example of the antenna pattern of the SL antenna 120. When the SL antenna 120 is perpendicular to the horizontal plane, the horizontally polarized waves of the SL antenna 120 are omnidirectional, as shown by the graph of the horizontally polarized waves of the SL antenna 120, and the vertically polarized waves of the SL antenna 120 have directionality, as shown by the graph of the vertically polarized waves of the SL antenna 120.

[0043] 3 is an explanatory diagram for explaining an example of a mounting method for mounting an antenna on the flying body 100. Here, the mounting method for mounting the SL antenna 120 on the flying body 100 will be mainly explained, assuming that the time axis does not change.

[0044] 3 is an explanatory diagram illustrating an example of a case where the SL antenna 120 is mounted horizontally on the aircraft 100. When the SL antenna 120 is mounted horizontally on the aircraft 100, the SL antenna 120 is parallel to the horizontal plane.

[0045] When the SL antenna 120 is mounted horizontally on the aircraft 100, the horizontally polarized waves of the SL antenna 120 are directional and the vertically polarized waves of the SL antenna 120 are omnidirectional. Therefore, as shown in the left diagram of Figure 3, the footprint 124 of the SL wireless communication area 122 has a rectangular shape. Here, the footprint is defined as a wireless communication area formed on a horizontal plane.

[0046] 3 is an explanatory diagram illustrating an example of a case where the SL antenna 120 is mounted vertically on the aircraft 100. When the SL antenna 120 is mounted vertically on the aircraft 100, the SL antenna 120 is perpendicular to the horizontal plane.

[0047] When the SL antenna 120 is mounted vertically on the aircraft 100, the horizontally polarized waves of the SL antenna 120 are omnidirectional and the vertically polarized waves of the SL antenna 120 are directional. Therefore, as shown in the right diagram of Figure 3, the footprint 124 of the SL wireless communication area 122 has a circular ring shape.

[0048] 4 is an explanatory diagram illustrating an example of the relationship between the footprint and the mounting method of an antenna on the aircraft 100. Here, the explanation will be mainly focused on a case where the information processing device 200 simulates the footprint 124 when the SL antenna 120 is mounted horizontally on the aircraft 100 and the footprint 124 when the SL antenna 120 is mounted vertically on the aircraft 100, assuming that the aircraft 100 is flying in a circular motion on an orbit 150.

[0049] The upper diagram of FIG. 4 is an explanatory diagram illustrating an example in which the information processing device 200 simulates the footprint 124 when the SL antenna 120 is mounted horizontally on the aircraft 100. As described above, the shape of the footprint 124 when the SL antenna 120 is mounted horizontally on the aircraft 100 is rectangular. Therefore, as shown in the upper diagram of FIG. 4, as the aircraft 100 performs a circular flight, the service target area 60 changes from being included in the footprint 124 to being not included in the footprint 124. This means that when the SL antenna 120 is mounted horizontally on the aircraft 100, there is no area that is always included in the SL wireless communication area 122 while the aircraft 100 is performing a circular flight. Therefore, the information processing device 200 simulates that when the SL antenna 120 is mounted horizontally on the aircraft 100, there is no area that is always available for communication while the aircraft 100 is performing a circular flight.

[0050] The lower diagram of FIG. 4 is an explanatory diagram illustrating an example in which the information processing device 200 simulates the footprint 124 when the SL antenna 120 is mounted vertically on the aircraft 100. As described above, the shape of the footprint 124 when the SL antenna 120 is mounted vertically on the aircraft 100 is a circular ring. Therefore, as shown in the lower diagram of FIG. 4, even when the aircraft 100 is flying in a circular motion, the coverage area 60 can remain included in the footprint 124. This means that when the SL antenna 120 is mounted vertically on the aircraft 100, there is an area that is always included in the SL wireless communication area 122 while the aircraft 100 is flying in a circular motion. Therefore, the information processing device 200 simulates that when the SL antenna 120 is mounted vertically on the aircraft 100, there is always an area in which communication is possible while the aircraft 100 is flying in a circular motion.

[0051] When the SL antenna 120 is mounted horizontally on the aircraft 100, there is no area where communication is possible while the aircraft 100 is in a circular flight. In contrast, when the SL antenna 120 is mounted vertically on the aircraft 100, there is always an area where communication is possible while the aircraft 100 is in a circular flight. Based on the above, the information processing device 200 determines, based on the simulation results, to adopt "vertical mounting" as the mounting method for the SL antenna 120 on the aircraft 100 so that the horizontally polarized waves of the SL antenna 120 are omnidirectional. For the same reasons as for deciding to adopt "vertical mounting" as the mounting method for the SL antenna 120 on the aircraft 100, the information processing device 200 determines, based on the simulation results, to adopt "vertical mounting" as the mounting method for the FL antenna 140 on the aircraft 100 so that the horizontally polarized waves of the FL antenna 140 are omnidirectional.

[0052] FIG. 5 is an explanatory diagram illustrating an example of a turning flight trajectory of the aircraft 100. The aircraft 100 makes a turning flight on a circular orbit, for example. The aircraft 100 makes a turning flight on a figure-eight orbit, for example. The aircraft 100 makes a turning flight on a rectangular orbit, for example. The aircraft 100 makes a turning flight on a D-shaped orbit, for example. The aircraft 100 may make a turning flight on an orbit of any other shape. Here, the circular orbit, the figure-eight orbit, the rectangular orbit, and the D-shaped orbit will be mainly described.

[0053] The "circular orbit" is primarily characterized by being a basic orbit and the radius of the circular orbit depending on the flight speed. The footprint formed when the aircraft 100 flies in a circular orbit varies depending on the flight altitude, flight speed, and radius of the circular orbit of the aircraft 100. Furthermore, when the aircraft 100 flies in a circular orbit, the footprint can be formed without controlling the antenna.

[0054] The "figure-eight trajectory" is primarily characterized by combining two circular trajectories. The size of the footprint formed when the aircraft 100 circles on the figure-eight trajectory is more than twice the size of the footprint formed when the aircraft 100 circles on a circular trajectory. Furthermore, when the aircraft 100 circles on the figure-eight trajectory, the antenna must be controlled to form the footprint.

[0055] The "rectangular trajectory" is primarily characterized by a combination of a circular trajectory and a straight trajectory. The size of the footprint formed when the aircraft 100 circles on the rectangular trajectory is more than twice the size of the footprint formed when the aircraft 100 circles on a circular trajectory. Furthermore, when the aircraft 100 circles on the rectangular trajectory, the antenna must be controlled to form the footprint.

[0056] The "D-shaped trajectory" is characterized by the fact that it combines a circular trajectory and a straight trajectory, and that it is not possible to draw a right-angle trajectory, so in reality it is closer to a rectangular trajectory. The size of the footprint formed when the aircraft 100 makes a circular flight on a D-shaped trajectory is more than twice the size of the footprint formed when the aircraft 100 makes a circular flight on a D-shaped trajectory. Furthermore, when the aircraft 100 makes a circular flight on a D-shaped trajectory, the antenna must be controlled to form the footprint.

[0057] As mentioned above, a footprint can be formed without controlling the antenna only when the flying object 100 is flying in a circular orbit. From the above, the information processing device 200 determines that the flying object 100 should fly in a circular orbit.

[0058] 6 is an explanatory diagram illustrating an example of aircraft performance information for the aircraft 100, recommended conditions for the aircraft 100 when conducting a demonstration experiment, and the relationship between the flight speed, the radius of the circular orbit, and the bank angle of the aircraft 100. Here, the flight speed of the aircraft 100 is the flight speed of the aircraft 100 when the aircraft 100 is performing a turning flight, and the flight altitude of the aircraft 100 is the flight altitude of the aircraft 100 when the aircraft 100 is performing a turning flight. The bank angle is the attitude angle of the aircraft 100 when the aircraft 100 is performing a turning flight.

[0059] The upper diagram of Fig. 6 is an explanatory diagram for explaining an example of aircraft performance information of the aircraft 100. The aircraft performance information of the aircraft 100 shown in the upper diagram of Fig. 6 is as follows.

[0060] The minimum flight altitude of the aircraft 100 is 1000 ft (304.8 m). The minimum flight speed of the aircraft 100 is 170 km / h. The allowable bank angle of the aircraft 100 is 15°.

[0061] The middle diagram in Fig. 6 is an explanatory diagram for explaining an example of recommended conditions for the aircraft 100 when conducting a demonstration experiment. The recommended conditions for the aircraft 100 when conducting the demonstration experiment shown in the middle diagram in Fig. 6 are as follows.

[0062] When conducting a demonstration experiment, the recommended flight conditions for the flying object 100 to fly in a circular flight are "over the sea only." When conducting a demonstration experiment, the recommended flight altitude for the flying object 100 is "500 m or more." When conducting a demonstration experiment, the recommended flight speed for the flying object 100 is "180 km / h or more."

[0063] The lower diagram of Figure 6 is an explanatory diagram illustrating an example of the relationship between the flight speed, the radius of the circular orbit, and the bank angle of the flying body 100. The relationship between the flight speed, the radius of the circular orbit, and the bank angle of the flying body 100 shown in the lower diagram of Figure 6 is as follows:

[0064] If the flight speed of the aircraft 100 is 180 km / h and the radius of the circular orbit of the aircraft 100 is 1000 m, the bank angle of the aircraft 100 is 14.9418°. If the flight speed of the aircraft 100 is 180 km / h and the radius of the circular orbit of the aircraft 100 is 1500 m, the bank angle of the aircraft 100 is 9.8392°. If the flight speed of the aircraft 100 is 180 km / h and the radius of the circular orbit of the aircraft 100 is 2000 m, the bank angle of the aircraft 100 is 7.3480°.

[0065] If the flight speed of the aircraft 100 is 190 km / h and the radius of the circular orbit of the aircraft 100 is 1000 m, the bank angle of the aircraft 100 is 16.7386°. If the flight speed of the aircraft 100 is 190 km / h and the radius of the circular orbit of the aircraft 100 is 1500 m, the bank angle of the aircraft 100 is 10.9888°. If the flight speed of the aircraft 100 is 190 km / h and the radius of the circular orbit of the aircraft 100 is 2000 m, the bank angle of the aircraft 100 is 8.1980°.

[0066] If the flight speed of the aircraft 100 is 200 km / h and the radius of the circular orbit of the aircraft 100 is 1000 m, the bank angle of the aircraft 100 is 18.6660°. If the flight speed of the aircraft 100 is 200 km / h and the radius of the circular orbit of the aircraft 100 is 1500 m, the bank angle of the aircraft 100 is 12.2098°. If the flight speed of the aircraft 100 is 200 km / h and the radius of the circular orbit of the aircraft 100 is 2000 m, the bank angle of the aircraft 100 is 9.0977°.

[0067] If the flight speed of the aircraft 100 is 210 km / h and the radius of the circular orbit of the aircraft 100 is 1000 m, the bank angle of the aircraft 100 is 20.7344°. If the flight speed of the aircraft 100 is 210 km / h and the radius of the circular orbit of the aircraft 100 is 1500 m, the bank angle of the aircraft 100 is 13.5050°. If the flight speed of the aircraft 100 is 210 km / h and the radius of the circular orbit of the aircraft 100 is 2000 m, the bank angle of the aircraft 100 is 10.0483°.

[0068] If the flight speed of the aircraft 100 is 220 km / h and the radius of the circular orbit of the aircraft 100 is 1000 m, the bank angle of the aircraft 100 is 22.9563°. If the flight speed of the aircraft 100 is 220 km / h and the radius of the circular orbit of the aircraft 100 is 1500 m, the bank angle of the aircraft 100 is 14.8776°. If the flight speed of the aircraft 100 is 220 km / h and the radius of the circular orbit of the aircraft 100 is 2000 m, the bank angle of the aircraft 100 is 11.05116°.

[0069] The bank angle of the aircraft 100 when the flight speed of the aircraft 100 is 190 km / h or greater and the radius of the circular orbit of the aircraft 100 is 1000 m is greater than the allowable bank angle of the aircraft 100 (= 15°). Therefore, the bank angle of the aircraft 100 when the flight speed of the aircraft 100 is 190 km / h or greater and the radius of the circular orbit of the aircraft 100 is 1000 m is not allowable. From the above, the information processing device 200 determines to adopt, as preconditions for simulating the circular orbit of the aircraft 100, "flight altitude of the aircraft 100 = 500 m or greater," "flight speed of the aircraft 100 = 180 to 200 km / h," and "radius of the circular orbit of the aircraft 100 = 1000 m or greater (however, when the radius of the circular orbit of the aircraft 100 = 1000 m, the flight speed of the aircraft 100 = 180 km / h only)."

[0070] 7 is an explanatory diagram for explaining an example of link budget conditions. Here, the link budget includes the link budget of the service link and the link budget of the feeder link. The link budgets shown in FIG. 7 are as follows:

[0071] The minimum receiving sensitivity (Reference Signal Received Power: RSRP) is "-115 dBm". The margin is "0 dB". The allowable antenna gain is "allowed up to half of half value (power: -6 dB)". The antenna gain of the gateway 40 is "peak 6 dBi". The antenna gain of the FL antenna 140 is "peak 6 dBi". The antenna gain of the SL antenna 120 is "peak 6 dBi". The antenna gain of the communication terminal 300 is "0 dB".

[0072] 8 is an explanatory diagram illustrating an example of the relationship between the flight altitude and footprint of the flying object 100. Here, the explanation is based on the assumption that the flying object 100 turns at a single point. Note that the flying object 100 turning at a single point may mean that the radius of the circular orbit of the flying object 100 is 0 m.

[0073] r i is the inner diameter of the footprint 124. i may be the distance from the center c of the footprint 124 to the position where the radio wave radiated by the SL antenna 120 and having a gain of -6 dB relative to the peak value reaches the horizontal plane. Note that the center c of the footprint 124 may be the intersection of the center line of the SL antenna 120 parallel to the flight altitude direction and the horizontal plane.

[0074] r o is the outer diameter of the footprint 124. o may be the distance from the center c of the footprint 124 to the maximum reach in the horizontal plane of the radio waves radiated by the SL antenna 120 to meet the link budget requirements of the service link.

[0075] w is the width of the footprint 124. w is the width of the footprint 124.o and r i and w=r o -r i Meet the following.

[0076] As the flying altitude of the flying object 100 increases, w decreases. As w decreases, the area of ​​the footprint 124 decreases. When the flying altitude of the flying object 100 exceeds a certain level, the SL antenna 120 is no longer able to form the footprint 124. This is because, as the flying altitude of the flying object 100 increases, the free space loss of the radio waves radiated by the SL antenna 120 increases until they reach the horizontal plane, and as a result, fewer of the radio waves reach the horizontal plane to meet the link budget requirements of the service link. From the above, it can be said that "the lower the flying altitude of the flying object 100, the larger the area of ​​the footprint 124 that can be formed."

[0077] 9 is an explanatory diagram illustrating an example of the relationship between the footprint and the radius of the circular orbit of the flying object 100. Here, the description will be given assuming that the flying altitude of the flying object 100 is constant.

[0078] R is the radius of the circular orbit of the air vehicle 100. Therefore, 2R is the diameter of the circular orbit of the air vehicle 100.

[0079] When R=0, the position of the SL antenna 120 does not change, and therefore the position of the footprint 124 formed by the SL antenna 120 does not change. w0 is the width of the footprint 124 formed by the SL antenna 120 when R=0.

[0080] When R>0, the position of SL antenna 120 changes, and therefore the position of footprint 124 formed by SL antenna 120 changes. w' is the width of footprint 126 formed by SL antenna 120 regardless of the position of air vehicle 100 while air vehicle 100 is in a circular orbital maneuver when R>0.

[0081] As R becomes longer, w' becomes shorter. As w' becomes shorter, the area of ​​footprint 126 becomes smaller. And when R exceeds a certain length, SL antenna 120 can no longer form footprint 126. This is because the amount of change in the position of the footprint formed by SL antenna 120 increases as R becomes longer. From the above, it can be said that "the shorter the radius of the circular orbit of aircraft 100, the wider the area of ​​the footprint that can be formed."

[0082] 10 is an explanatory diagram illustrating an example of a simulation result of a link budget of a feeder link and an FL wireless communication area. Here, the link budget of a feeder link is assumed to be the link budget of the downlink of the feeder link.

[0083] The upper diagram of Fig. 10 is an explanatory diagram for explaining an example of a link budget for the downlink of the feeder link. The link budget for the downlink of the feeder link shown in the upper diagram of Fig. 10 is as follows.

[0084] The minimum receiving sensitivity (RSRP) is "-115 dBm." The antenna gain of the FL antenna 140 is "inner diameter: half of half value (0 dBi), outer diameter: half value (3 dBi)." The antenna gain of the gateway 40 is "peak 6 dBi." The transmission power of the FL antenna 140 is "1 W (30 dBm)." The margin is "0 dB."

[0085] 10 is an explanatory diagram for explaining an example of a simulation result in which the information processing device 200 simulates an FL wireless communication area. The simulation result by the information processing device 200 shown in the lower diagram of FIG. 10 is as follows.

[0086] When the flight altitude of the aircraft 100 is "500 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the FL wireless communication area is "1538.8 m", the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the inner diameter of the footprint of the FL wireless communication area is "135.0 dB", the outer diameter of the footprint of the FL wireless communication area is "14350.4 m", and the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the outer diameter of the footprint of the FL wireless communication area is "149.0 dB". When the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the FL wireless communication area is "3077.7 m", the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the inner diameter of the footprint of the FL wireless communication area is "141.1 dB", the outer diameter of the footprint of the FL wireless communication area is "14324.2 m", and the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the outer diameter of the footprint of the FL wireless communication area is "149.0 dB". When the flight altitude of the aircraft 100 is "1500 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the FL wireless communication area is "4616.5 m", the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the inner diameter of the footprint of the FL wireless communication area is "144.6 dB", the outer diameter of the footprint of the FL wireless communication area is "14280.5 m", and the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the outer diameter of the footprint of the FL wireless communication area is "149.0 dB".When the flight altitude of the aircraft 100 is "2000 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the FL wireless communication area is "6155.4 m", the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the inner diameter of the footprint of the FL wireless communication area is "147.1 dB", the outer diameter of the footprint of the FL wireless communication area is "14219.1 m", and the attenuation of the radio waves radiated by the FL antenna 140 while propagating the distance of the outer diameter of the footprint of the FL wireless communication area is "149.0 dB".

[0087] If the flight altitude of aircraft 100 is "500 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the FL wireless communication area is "1538.8 m", the outer diameter of the footprint of the FL wireless communication area is "12350.4 m", and the width of the footprint of the FL wireless communication area is "12350.4 m - 1538.8 m = 10811.6 m". If the flight altitude of aircraft 100 is "500 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the FL wireless communication area is "1538.8 m", the outer diameter of the footprint of the FL wireless communication area is "11350.4 m", and the width of the footprint of the FL wireless communication area is "11350.4 m - 1538.8 m = 9811.6 m". If the flight altitude of the aircraft 100 is "500 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the FL wireless communication area is "1538.8 m", the outer diameter of the footprint of the FL wireless communication area is "10350.4 m", and the width of the footprint of the FL wireless communication area is "10350.4 m - 1538.8 m = 8811.6 m".

[0088] When the flight altitude of aircraft 100 is "1000 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the FL wireless communication area is "3077.7 m", the outer diameter of the footprint of the FL wireless communication area is "12324.2 m", and the width of the footprint of the FL wireless communication area is "12324.2 m - 3077.7 m = 9246.6 m". When the flight altitude of aircraft 100 is "1000 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the FL wireless communication area is "3077.7 m", the outer diameter of the footprint of the FL wireless communication area is "11324.2 m", and the width of the footprint of the FL wireless communication area is "11324.2 m - 3077.7 m = 8246.6 m". If the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the FL wireless communication area is "3077.7 m", the outer diameter of the footprint of the FL wireless communication area is "10324.2 m", and the width of the footprint of the FL wireless communication area is "10324.2 m - 3077.7 m = 7246.6 m".

[0089] If the flight altitude of aircraft 100 is "1500 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the FL wireless communication area is "4616.5 m", the outer diameter of the footprint of the FL wireless communication area is "12280.5 m", and the width of the footprint of the FL wireless communication area is "12280.5 m - 4616.5 m = 7664.0 m". If the flight altitude of aircraft 100 is "1500 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the FL wireless communication area is "4616.5 m", the outer diameter of the footprint of the FL wireless communication area is "11280.5 m", and the width of the footprint of the FL wireless communication area is "11280.5 m - 4616.5 m = 6664.0 m". If the flight altitude of the aircraft 100 is "1500 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the FL wireless communication area is "4616.5 m", the outer diameter of the footprint of the FL wireless communication area is "10280.5 m", and the width of the footprint of the FL wireless communication area is "10280.5 m - 4616.5 m = 5664.0 m".

[0090] If the flight altitude of aircraft 100 is "2000 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the FL wireless communication area is "6155.4 m", the outer diameter of the footprint of the FL wireless communication area is "12219.1 m", and the width of the footprint of the FL wireless communication area is "12219.1 m - 6155.4 m = 6063.8 m". If the flight altitude of aircraft 100 is "2000 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the FL wireless communication area is "6155.4 m", the outer diameter of the footprint of the FL wireless communication area is "11219.1 m", and the width of the footprint of the FL wireless communication area is "11219.1 m - 6155.4 m = 5063.8 m". If the flight altitude of the aircraft 100 is "2000 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the FL wireless communication area is "6155.4 m", the outer diameter of the footprint of the FL wireless communication area is "10219.1 m", and the width of the footprint of the FL wireless communication area is "10219.1 m - 6155.4 m = 4063.8 m".

[0091] The simulation results by the information processing device 200 shown in the lower diagram of Fig. 10 show that the width of the footprint of the FL wireless communication area has a positive value for all combinations of the flight altitude and the radius of the circular orbit of the aircraft 100. This means that for all combinations of the flight altitude and the radius of the circular orbit of the aircraft 100, the aircraft 100 can form a footprint of the FL wireless communication area that satisfies the link budget requirement of the feeder link downlink.

[0092] 11 is an explanatory diagram illustrating an example of the link budget of the service link and the simulation results of the SL wireless communication area. Here, the link budget of the service link is assumed to be the link budget of the uplink of the service link.

[0093] The upper diagram of Fig. 11 is an explanatory diagram for explaining an example of the link budget of the uplink of the service link. The link budget of the uplink of the service link shown in the upper diagram of Fig. 11 is as follows.

[0094] The minimum receiving sensitivity (RSRP) is "-115 dBm". The antenna gain of the communication terminal 300 is "0 dBi". The antenna gain of the SL antenna 120 is "half value (3 dBi)". The transmission power of the communication terminal 300 is "200 mW (23 dBm)". The margin is "0 dB".

[0095] The lower diagram of Fig. 11 is an explanatory diagram for explaining an example of the simulation results obtained by simulating the SL wireless communication area by the information processing device 200. The simulation results obtained by the information processing device 200 shown in the lower diagram of Fig. 11 are as follows.

[0096] When the flight altitude of the aircraft 100 is "500 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the SL wireless communication area is "1373.7 m", the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the inner diameter of the footprint of the SL wireless communication area is "129.6 dB", the outer diameter of the footprint of the SL wireless communication area is "5406.5 m", and the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the outer diameter of the footprint of the SL wireless communication area is "141.0 dB". When the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the SL wireless communication area is "2747.5 m", the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the inner diameter of the footprint of the SL wireless communication area is "135.6 dB", the outer diameter of the footprint of the SL wireless communication area is "5336.7 m", and the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the outer diameter of the footprint of the SL wireless communication area is "141.0 dB". When the flight altitude of the aircraft 100 is "1500 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the SL wireless communication area is "4121.2 m", the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the inner diameter of the footprint of the SL wireless communication area is "139.2 dB", the outer diameter of the footprint of the SL wireless communication area is "5218.2 m", and the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the outer diameter of the footprint of the SL wireless communication area is "141.0 dB".When the flight altitude of the aircraft 100 is "2000 m" and the radius of the circular orbit of the aircraft 100 is "0 m", the inner diameter of the footprint of the SL wireless communication area is "5495.0 m", the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the inner diameter of the footprint of the SL wireless communication area is "141.7 dB", the outer diameter of the footprint of the SL wireless communication area is "5047.8 m", and the attenuation of the radio waves radiated by the SL antenna 120 while propagating the distance of the outer diameter of the footprint of the SL wireless communication area is "141.0 dB".

[0097] If the flight altitude of aircraft 100 is "500 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the SL wireless communication area is "1373.7 m", the outer diameter of the footprint of the SL wireless communication area is "3406.5 m", and the width of the footprint of the SL wireless communication area is "3406.5 m - 1373.7 m = 2032.7 m". If the flight altitude of aircraft 100 is "500 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the SL wireless communication area is "1373.7 m", the outer diameter of the footprint of the SL wireless communication area is "2406.5 m", and the width of the footprint of the SL wireless communication area is "2406.5 m - 1373.7 m = 1032.7 m". If the flight altitude of the aircraft 100 is "500 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the SL wireless communication area is "1373.7 m", the outer diameter of the footprint of the SL wireless communication area is "1406.5 m", and the width of the footprint of the SL wireless communication area is "1406.5 m - 1373.7 m = 32.7 m".

[0098] When the flight altitude of aircraft 100 is "1000 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the SL wireless communication area is "2747.5 m", the outer diameter of the footprint of the SL wireless communication area is "3336.7 m", and the width of the footprint of the SL wireless communication area is "3336.7 m - 2747.5 m = 589.2 m". When the flight altitude of aircraft 100 is "1000 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the SL wireless communication area is "2747.5 m", the outer diameter of the footprint of the SL wireless communication area is "2336.7 m", and the width of the footprint of the SL wireless communication area is "2336.7 m - 2747.5 m = -410.8 m". If the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the SL wireless communication area is "2747.5 m", the outer diameter of the footprint of the SL wireless communication area is "1336.7 m", and the width of the footprint of the SL wireless communication area is "1336.7 m - 2747.5 m = -1410.8 m".

[0099] If the flight altitude of aircraft 100 is "1500 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the SL wireless communication area is "4121.2 m", the outer diameter of the footprint of the SL wireless communication area is "3218.2 m", and the width of the footprint of the SL wireless communication area is "3218.2 m - 4121.2 m = -903.0 m". If the flight altitude of aircraft 100 is "1500 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the SL wireless communication area is "4121.2 m", the outer diameter of the footprint of the SL wireless communication area is "2218.2 m", and the width of the footprint of the SL wireless communication area is "2218.2 m - 4121.2 m = -1903.0 m". If the flight altitude of the aircraft 100 is "1500 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the SL wireless communication area is "4121.2 m", the outer diameter of the footprint of the SL wireless communication area is "1218.2 m", and the width of the footprint of the SL wireless communication area is "1218.2 m - 4121.2 m = -2903.0 m".

[0100] If the flight altitude of aircraft 100 is "2000 m" and the radius of the circular orbit of aircraft 100 is "1000 m", the inner diameter of the footprint of the SL wireless communication area is "5495.0 m", the outer diameter of the footprint of the SL wireless communication area is "3047.8 m", and the width of the footprint of the SL wireless communication area is "3047.8 m - 5495.0 m = -2447.2 m". If the flight altitude of aircraft 100 is "2000 m" and the radius of the circular orbit of aircraft 100 is "1500 m", the inner diameter of the footprint of the SL wireless communication area is "5495.0 m", the outer diameter of the footprint of the SL wireless communication area is "2047.8 m", and the width of the footprint of the SL wireless communication area is "2047.8 m - 5495.0 m = -3447.2 m". If the flight altitude of the aircraft 100 is "2000 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the inner diameter of the footprint of the SL wireless communication area is "5495.0 m", the outer diameter of the footprint of the SL wireless communication area is "1047.8 m", and the width of the footprint of the SL wireless communication area is "1047.8 m - 5495.0 m = -4447.2 m".

[0101] 11 shows that, of all the combinations of the flight altitude and the radius of the circular orbit of the aircraft 100, only the combinations of flight altitude of the aircraft 100 = 500 m and the radius of the circular orbit of the aircraft 100 = 1000 m, flight altitude of the aircraft 100 = 500 m and the radius of the circular orbit of the aircraft 100 = 1500 m, flight altitude of the aircraft 100 = 500 m and the radius of the circular orbit of the aircraft 100 = 2000 m, and flight altitude of the aircraft 100 = 1000 m and the radius of the circular orbit of the aircraft 100 = 1000 m have a positive value for the width of the footprint of the SL wireless communication area. This means that only the combinations of flight altitude and radius of the circular orbit of the aircraft 100 have a positive value for the width of the footprint of the SL wireless communication area, and the aircraft 100 can form a footprint of the SL wireless communication area that satisfies the link budget requirement of the uplink of the service link.

[0102] 10 and 11 show that the combination of the flight altitude and the radius of the circular orbit of the flying object 100 that can form the footprint of the FL wireless communication area is not limited, but the combination of the flight altitude and the radius of the circular orbit of the flying object 100 that can form the footprint of the SL wireless communication area is limited. This is because the transmission power (=200 mW) of the communication terminal 300 is smaller than the transmission power (=1 W) of the FL antenna 140.

[0103] 12 is an explanatory diagram for explaining an example of the relationship between the flight altitude and the radius of the circular orbit of the flying body 100 and the footprint. Here, an example will be mainly explained in which the information processing device 200 determines the flight altitude and the radius of the circular orbit of the flying body 100 based on the simulation results by the information processing device 200 shown in FIG.

[0104] When the flight altitude of the aircraft 100 is 500 m and the radius of the circular orbit of the aircraft 100 is 1000 m, the aircraft 100 forms a footprint of an SL wireless communication area with a width of 2032.7 m. When the flight altitude of the aircraft 100 is 500 m and the radius of the circular orbit of the aircraft 100 is 1500 m, the aircraft 100 forms a footprint of an SL wireless communication area with a width of 1032.7 m. When the flight altitude of the aircraft 100 is 500 m and the radius of the circular orbit of the aircraft 100 is 2000 m, the aircraft 100 forms a footprint of an SL wireless communication area with a width of 32.7 m.

[0105] If the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "1000 m", the aircraft 100 forms a footprint of an SL wireless communication area with a width of "589.2 m". If the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "1500 m", the aircraft 100 cannot form a footprint of an SL wireless communication area. If the flight altitude of the aircraft 100 is "1000 m" and the radius of the circular orbit of the aircraft 100 is "2000 m", the aircraft 100 cannot form a footprint of an SL wireless communication area.

[0106] As shown in Figure 12, when the flight altitude of the aircraft 100 is "500 m" and the radius of the circular orbit of the aircraft 100 is "1000 m," the aircraft 100 can form the widest SL wireless communication area footprint. However, as shown in Figure 6, when the flight altitude of the aircraft 100 is "500 m" and the radius of the circular orbit of the aircraft 100 is "1000 m," even if the flight speed of the aircraft 100 is "180 km / h," the bank angle of the aircraft 100 is "14.9418°," and the bank angle margin is small. From the above, the information processing device 200 determines to adopt "500 m" as the flight altitude of the aircraft 100 and "1500 m" as the radius of the circular orbit of the aircraft 100.

[0107] 13 is an explanatory diagram for explaining an example of the decisions made by the information processing device 200. Based on the results of the simulation described above, the information processing device 200 has decided on the "antenna mounting method," "trajectory of the flying body 100," "flight speed of the flying body 100," "radius of the orbit of the flying body 100," and "flight altitude of the flying body 100." The decisions made by the information processing device 200 shown in FIG. 13 are as follows:

[0108] In the item "antenna mounting method," the information processing device 200 determined "vertical mounting" as the mounting method for mounting the SL antenna 120 and the FL antenna 140 on the flying body 100 from among the candidates "horizontal mounting" and "vertical mounting." In the item "trajectory of flying body 100," the information processing device 200 determined "circular orbit" as the trajectory for the circular flight of the flying body 100 from among the candidates "circular orbit," "figure-eight orbit," "rectangular orbit," and "D-shaped orbit." In the item "flight speed of flying body 100," the information processing device 200 determined "180 km / h" as the flight speed of the flying body 100 when the flying body 100 is flying in a circular flight from among the candidates "170 km / h or more." For the item "Radius of the orbit of the flying body 100," the information processing device 200 determined "1500 m" from among the candidates "1000 m," "1500 m," and "2000 m" as the radius of the circular orbit of the flying body 100 when the flying body 100 is flying in a circle. For the item "Flight altitude of the flying body 100," the information processing device 200 determined "500 m" from among the candidates "500 m," "1000 m," and "1500 m" as the flight altitude of the flying body 100 when the flying body 100 is flying in a circle.

[0109] Based on the above-mentioned determinations, the information processing device 200 may simulate the SL wireless communication area 122 formed by the SL beam irradiated by the SL antenna 120 while the flying object 100 is making a circular flight. Then, based on the provision target area information and the simulation results of the SL wireless communication area, the information processing device 200 may determine the trajectory of the flying object 100 so that the provision target area 60 is included in the SL wireless communication area 122 while the flying object 100 is making a circular flight.

[0110] Based on the above-mentioned determinations, the information processing device 200 may further simulate an FL wireless communication area formed by the FL beam irradiated by the FL antenna 140 while the flying object 100 is making a circular flight. Then, based on the installation position information and the simulation results of the FL wireless communication area, the information processing device 200 may determine the trajectory of the flying object 100 so that the service target region 60 is included in the SL wireless communication area 122 and the installation position of the gateway 40 is included in the FL wireless communication area while the flying object 100 is making a circular flight.

[0111] In the past, active research has been conducted into technologies for using airborne base stations to provide wireless communication services to areas where wireless communication services are unavailable, such as when wireless base stations are damaged in a large-scale disaster or when large numbers of people gather at an event venue, etc. In recent years, with the emergence of unmanned aerial vehicles capable of high-speed flight on the market, research into this technology has become even more active.

[0112] When using airborne base stations to provide wireless communication services to a target area, the greater the number of airborne base stations, the more flexible the wireless communication services can be provided to multiple target areas in different locations or a wider target area. Therefore, the greater the number of airborne base stations, the more flexible the wireless communication services can be provided using the airborne base stations. Therefore, in order to provide more flexible wireless communication services using airborne base stations, it is desirable to be able to manufacture more airborne base stations within a limited budget. Therefore, in order to reduce the manufacturing cost of airborne base stations, the use of collinear antennas mounted on existing balloon base stations as antennas mounted on airborne base stations has been considered. However, unlike balloon base stations that fly at fixed points, airborne base stations fly in a circular flight. Furthermore, the flight altitude of the airborne base station when providing wireless communication services is higher than the flight altitude of the balloon base station when providing wireless communication services. Therefore, the wireless communication area formed by an airborne base station equipped with a collinear antenna has different characteristics from the wireless communication area formed by a balloon base station equipped with a collinear antenna. Therefore, it is desirable for an airborne base station equipped with a collinear antenna mounted on an existing balloon base station to be able to provide wireless communication services to a target area while flying in a circular flight.

[0113] In contrast, in the system 10 according to the present embodiment, the information processing device 200 simulates the SL wireless communication area 122 while the aircraft 100 is making a circular flight, based on SL antenna performance information of the SL antenna 120, which is a collinear antenna, and aircraft performance information of the aircraft 100 equipped with the SL antenna 120. Then, the information processing device 200 determines the trajectory of the aircraft 100 based on the service area information and the simulation results of the SL wireless communication area 122, so that the service area 60 is included in the SL wireless communication area 122 while the aircraft 100 is making a circular flight. The aircraft 100 forms the SL wireless communication area 122 while making a circular flight according to the trajectory of the aircraft 100 determined by the information processing device 200, thereby enabling wireless communication services to the service area 60 while making a circular flight. As a result, the system 10 according to the present embodiment allows an aircraft base station equipped with a collinear antenna mounted on an existing balloon base station to provide wireless communication services to the service area while making a circular flight. Furthermore, when the colinear antenna mounted on an existing balloon base station is used as the antenna mounted on the air vehicle base station, the manufacturing cost of the air vehicle base station can be reduced compared to developing a new antenna for the air vehicle base station. As a result, the system 10 according to the present embodiment can reduce the manufacturing cost of an air vehicle base station that can provide wireless communication services to a target area while flying in a circular flight. As a result, the system 10 according to the present embodiment can contribute to the realization of providing more flexible wireless communication services using air vehicle base stations.

[0114] 14 schematically illustrates an example of the functional configuration of the information processing device 200. The information processing device 200 includes a storage unit 202, an acquisition unit 204, a simulation unit 206, a determination unit 208, and a control unit 210. Note that it is not essential that the information processing device 200 includes all of these components.

[0115] The storage unit 202 stores various types of information, such as installation location information of the gateway 40.

[0116] The storage unit 202 stores, for example, SL antenna performance information of the SL antenna 120. The SL antenna performance information includes, for example, SL antenna frequency band information indicating the frequency band of the SL antenna 120. The SL antenna performance information includes, for example, SL antenna antenna power information indicating the antenna power of the SL antenna 120. The SL antenna performance information includes, for example, SL antenna gain information indicating the antenna gain of the SL antenna 120. The SL antenna performance information includes, for example, SL antenna antenna type information indicating the antenna type of the SL antenna 120. The SL antenna performance information includes, for example, SL antenna horizontal plane half-width information indicating the horizontal plane half-width of the SL antenna 120. The SL antenna performance information includes, for example, SL antenna vertical plane half-width information indicating the vertical plane half-width of the SL antenna 120.

[0117] The storage unit 202 stores, for example, FL antenna performance information of the FL antenna 140. The FL antenna performance information includes, for example, FL antenna frequency band information indicating the frequency band of the FL antenna 140. The FL antenna performance information includes, for example, FL antenna antenna power information indicating the antenna power of the FL antenna 140. The FL antenna performance information includes, for example, FL antenna gain information indicating the antenna gain of the FL antenna 140. The FL antenna performance information includes, for example, FL antenna antenna type information indicating the antenna type of the FL antenna 140. The FL antenna performance information includes, for example, FL antenna horizontal plane half-width information indicating the horizontal plane half-width of the FL antenna 140. The FL antenna performance information includes, for example, FL antenna vertical plane half-width information indicating the vertical plane half-width of the FL antenna 140.

[0118] The storage unit 202 stores, for example, aircraft performance information of the aircraft 100. The aircraft performance information includes, for example, minimum flight altitude information indicating the minimum flight altitude of the aircraft 100 when performing a turning flight. The aircraft performance information includes, for example, minimum flight speed information indicating the minimum flight speed of the aircraft 100 when performing a turning flight. The aircraft performance information includes, for example, allowable bank angle information indicating the allowable bank angle of the aircraft 100 when performing a turning flight.

[0119] The storage unit 202 stores, for example, recommended condition information indicating recommended conditions for the flying object 100 when conducting a demonstration experiment. The recommended condition information includes, for example, recommended flight condition information indicating recommended flight conditions under which the flying object 100 will perform a circular flight when conducting a demonstration experiment. The recommended condition information includes, for example, recommended flight altitude information indicating a recommended flight altitude for the flying object 100 when conducting a demonstration experiment. The recommended condition information includes, for example, recommended flight speed information indicating a recommended flight speed for the flying object 100 when conducting a demonstration experiment.

[0120] The storage unit 202 stores, for example, link budget information indicating a link budget. The link budget information includes, for example, service link budget information indicating a link budget of a service link. The link budget information includes, for example, feeder link budget information indicating a link budget of a feeder link.

[0121] The link budget information includes, for example, minimum receiving sensitivity information indicating minimum receiving sensitivity (RSRP). The link budget information includes, for example, margin information indicating a margin. The link budget information includes, for example, allowable antenna gain information indicating an allowable antenna gain. The link budget information includes, for example, gateway gain information indicating the antenna gain of the gateway 40. The link budget information includes, for example, SL antenna gain information indicating the antenna gain of the SL antenna 120. The link budget information includes, for example, FL antenna gain information indicating the antenna gain of the FL antenna 140. The link budget information includes, for example, communication terminal gain information indicating the antenna gain of the communication terminal 300. The link budget information includes, for example, gateway transmission power information indicating the transmission power of the gateway 40. The link budget information includes, for example, SL antenna transmission power information indicating the transmission power of the SL antenna 120. The link budget information includes, for example, FL antenna transmission power information indicating the transmission power of the FL antenna 140. The link budget information includes, for example, communication terminal transmission power information indicating the transmission power of the communication terminal 300.

[0122] The acquisition unit 204 acquires various types of information. The acquisition unit 204 acquires various types of information by, for example, receiving the various types of information via the network 20. The acquisition unit 204 may acquire the various types of information by accepting input from a user of the information processing device 200 via an input unit provided in the information processing device 200. The user of the information processing device 200 may be a telecommunications carrier. The acquisition unit 204 may store the acquired various types of information in the storage unit 202.

[0123] The acquisition unit 204 acquires, for example, provision target area information indicating the provision target area 60. The acquisition unit 204 acquires, for example, provision target area information indicating two provision target areas 60 located at different positions.

[0124] The service target area 60 is, for example, an area affected by a disaster. The service target area 60 may be an area including a place where many users of wireless communication services are concentrated, such as an event venue.

[0125] The acquisition unit 204 acquires the provision target area information by, for example, receiving the provision target area information from a communication device owned by the user of the information processing device 200 via the network 20. The acquisition unit 204 may acquire the provision target area information by accepting input from the user of the information processing device 200 via an input unit included in the information processing device 200.

[0126] The acquiring unit 204 may acquire the disaster information from the disaster information management device 400, for example.

[0127] The simulation unit 206 executes various simulations based on various information stored in the storage unit 202, for example.

[0128] For example, in order to determine a mounting method for mounting the SL antenna 120 on the aircraft 100, the simulation unit 206 simulates the footprint of the SL wireless communication area 122 formed by the SL beam irradiated by the SL antenna 120 while the aircraft 100 is flying in a circle, based on the SL antenna performance information of the SL antenna 120. For example, the simulation unit 206 simulates the footprint of the SL wireless communication area 122 formed while the aircraft 100 is flying in a circle when the SL antenna 120 is mounted horizontally on the aircraft 100 and when the SL antenna 120 is mounted vertically on the aircraft 100.

[0129] For example, in order to determine a mounting method for mounting the FL antenna 140 on the aircraft 100, the simulation unit 206 simulates the footprint of the FL wireless communication area formed by the FL beam irradiated by the FL antenna 140 while the aircraft 100 is flying in a circle based on the FL antenna performance information of the FL antenna 140. For example, the simulation unit 206 simulates the footprint of the FL wireless communication area formed while the aircraft 100 is flying in a circle when the FL antenna 140 is mounted horizontally on the aircraft 100 and when the FL antenna 140 is mounted vertically on the aircraft 100.

[0130] The determining unit 208 determines various items, for example, based on the results of a simulation performed by the simulation unit 206.

[0131] The determination unit 208 determines the mounting method for the SL antenna 120 on the aircraft 100 based on the simulation results obtained by the simulation unit 206 simulating the footprints of the SL wireless communication area 122 formed while the aircraft 100 is flying in a circle when the SL antenna 120 is mounted horizontally on the aircraft 100 and when the SL antenna 120 is mounted vertically on the aircraft 100. The determination unit 208 may determine to mount the SL antenna 120 vertically on the aircraft 100 so that the horizontally polarized waves of the SL antenna 120 are omnidirectional.

[0132] The determination unit 208 determines the mounting method for the FL antenna 140 on the aircraft 100 based on the simulation results obtained by the simulation unit 206 simulating the footprints of the FL wireless communication area formed while the aircraft 100 is flying in a circle when the FL antenna 140 is mounted horizontally on the aircraft 100 and when the FL antenna 140 is mounted vertically on the aircraft 100. The determination unit 208 may determine to mount the FL antenna 140 vertically on the aircraft 100 so that the horizontally polarized waves of the FL antenna 140 are omnidirectional.

[0133] The determination unit 208, for example, determines a circular flight trajectory for the aircraft 100. For example, the determination unit 208 may determine the circular flight trajectory for the aircraft 100 from among a circular orbit, a figure-eight orbit, a rectangular orbit, and a D-shaped orbit in order to form a footprint without controlling an antenna mounted on the aircraft 100.

[0134] The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam irradiated by the SL antenna 120 while the aircraft 100 is flying in a circle, for example, based on the SL antenna performance information of the SL antenna 120 and the aircraft performance information of the aircraft 100. The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circle on a circular orbit, for example. The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circle on a circular orbit, for example, by deriving the inner and outer diameters of the footprint of the SL wireless communication area 122 based on the SL antenna gain information of the SL antenna 120. The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit, for example, by deriving the width of the footprint of the SL wireless communication area 122 from the difference between the outer diameter and the inner diameter of the footprint of the SL wireless communication area 122.

[0135] The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when, for example, the radius of the circular orbit of the aircraft 100 is the radius of each of the multiple circular orbit radii. The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when, for example, the radius of the circular orbit of the aircraft 100 is 0 m, the radius of the circular orbit of the aircraft 100 is 1000 m, the radius of the circular orbit of the aircraft 100 is 1500 m, and the radius of the circular orbit of the aircraft 100 is 2000 m.

[0136] The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when the flight speed of the aircraft 100 is each of a plurality of flight speeds. The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when the flight speed of the aircraft 100 is 180 km / h, when the flight speed of the aircraft 100 is 190 km / h, and when the flight speed of the aircraft 100 is 200 km / h. The plurality of flight speeds are assumed to be flight speeds equal to or greater than the minimum flight speed of the aircraft 100 indicated by the minimum flight speed information included in the aircraft performance information of the aircraft 100.

[0137] The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit based on, for example, minimum flight speed information and allowable bank angle information of the aircraft 100 included in the aircraft performance information of the aircraft 100. For example, when the flight speed of the aircraft 100 is each of a plurality of flight speeds equal to or greater than the minimum flight speed indicated by the minimum flight speed information, the simulation unit 206 derives the radius of the circular orbit of the aircraft 100 when the bank angle of the aircraft 100 is smaller than the allowable bank angle indicated by the allowable bank angle information, thereby simulating the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when the flight speed of the aircraft 100 is each flight speed.

[0138] The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when the flight altitude of the aircraft 100 is each of a plurality of flight altitudes. The simulation unit 206 simulates the SL wireless communication area 122 formed by the SL beam while the aircraft 100 is flying in a circular orbit when the flight altitude of the aircraft 100 is 500 m, when the flight altitude of the aircraft 100 is 1000 m, and when the flight altitude of the aircraft 100 is 1500 m. The plurality of flight altitudes are assumed to be flight altitudes equal to or higher than the minimum flight altitude of the aircraft 100 indicated by minimum flight altitude information included in the aircraft performance information of the aircraft 100.

[0139] The simulation unit 206 simulates the FL wireless communication area formed by the FL beam irradiated by the FL antenna 140 while the aircraft 100 is flying in a circular orbit, for example, based on FL antenna performance information of the FL antenna 140 and aircraft performance information of the aircraft 100. The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit, for example. The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit, for example, by deriving the inner and outer diameters of the footprint of the FL wireless communication area based on FL antenna gain information of the FL antenna 140. The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit, for example, by deriving the width of the footprint of the FL wireless communication area from the difference between the outer and inner diameters of the footprint of the FL wireless communication area.

[0140] The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when, for example, the radius of the circular orbit of the aircraft 100 is the radius of each of the multiple circular orbit radii. The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when, for example, the radius of the circular orbit of the aircraft 100 is 0 m, the radius of the circular orbit of the aircraft 100 is 1000 m, the radius of the circular orbit of the aircraft 100 is 1500 m, and the radius of the circular orbit of the aircraft 100 is 2000 m.

[0141] The simulation unit 206 simulates, for example, the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when the flight speed of the aircraft 100 is each of a plurality of flight speeds. The simulation unit 206 simulates, for example, the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when the flight speed of the aircraft 100 is 180 km / h, when the flight speed of the aircraft 100 is 190 km / h, and when the flight speed of the aircraft 100 is 200 km / h. The plurality of flight speeds are assumed to be flight speeds equal to or greater than the minimum flight speed of the aircraft 100 indicated by the minimum flight speed information included in the aircraft performance information of the aircraft 100.

[0142] The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit based on, for example, minimum flight speed information and allowable bank angle information of the aircraft 100 included in the aircraft performance information of the aircraft 100. For example, when the flight speed of the aircraft 100 is each of a plurality of flight speeds equal to or greater than the minimum flight speed indicated by the minimum flight speed information, the simulation unit 206 derives the radius of the circular orbit of the aircraft 100 when the bank angle of the aircraft 100 is smaller than the allowable bank angle indicated by the allowable bank angle information, thereby simulating the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when the flight speed of the aircraft 100 is each flight speed.

[0143] The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when the flight altitude of the aircraft 100 is each of a plurality of flight altitudes. The simulation unit 206 simulates the FL wireless communication area formed by the FL beam while the aircraft 100 is flying in a circular orbit when the flight altitude of the aircraft 100 is 500 m, when the flight altitude of the aircraft 100 is 1000 m, and when the flight altitude of the aircraft 100 is 1500 m. The plurality of flight altitudes are assumed to be flight altitudes equal to or higher than the minimum flight altitude of the aircraft 100 indicated by the minimum flight altitude information included in the aircraft performance information of the aircraft 100.

[0144] The determination unit 208 determines the flight speed of the aircraft 100 when the aircraft 100 is flying in a circle, for example, based on the simulation results of the simulation unit 206 simulating the SL wireless communication area 122. The determination unit 208 determines the flight altitude of the aircraft 100 when the aircraft 100 is flying in a circle, for example, based on the simulation results of the simulation unit 206 simulating the SL wireless communication area 122. The determination unit 208 determines the radius of the circular orbit of the aircraft 100 when the aircraft 100 is flying in a circle, for example, based on the simulation results of the simulation unit 206 simulating the SL wireless communication area 122.

[0145] The determination unit 208 determines the flight speed of the aircraft 100 when the aircraft 100 is flying in a circle, for example, based on the simulation results of the simulation unit 206 simulating the FL wireless communication area. The determination unit 208 determines the flight altitude of the aircraft 100 when the aircraft 100 is flying in a circle, for example, based on the simulation results of the simulation unit 206 simulating the FL wireless communication area. The determination unit 208 determines the radius of the circular orbit of the aircraft 100 when the aircraft 100 is flying in a circle, for example, based on the simulation results of the simulation unit 206 simulating the FL wireless communication area.

[0146] The determination unit 208 determines the trajectory of the aircraft 100 so that the provision target area 60 is included in the SL wireless communication area 122 while the aircraft 100 is flying in a circle, for example, based on the provision target area information and the simulation result of the simulation unit 206 simulating the SL wireless communication area 122. The determination unit 208 determines the trajectory of the aircraft 100 so that two provision target areas 60 in different positions, which are indicated by the provision target area information, are included in the SL wireless communication area 122 while the aircraft 100 is flying in a circle, for example.

[0147] The determination unit 208 determines the position of the center of the circular orbit of the aircraft 100, for example, while the aircraft 100 is flying in a circular orbit, so that the provision target area 60 is included in the SL wireless communication area 122. The determination unit 208 determines the flight altitude of the aircraft 100, for example, while the aircraft 100 is flying in a circular orbit, so that the provision target area 60 is included in the SL wireless communication area 122. The determination unit 208 determines the flight speed of the aircraft 100 and the radius of the circular orbit of the aircraft 100, for example, while the aircraft 100 is flying in a circular orbit, so that the provision target area 60 is included in the SL wireless communication area 122.

[0148] The determination unit 208 determines the trajectory of the aircraft 100 so that the installation position of the gateway 40 is included in the FL wireless communication area while the aircraft 100 is making a circular flight, for example, based on the installation position information of the gateway 40 and the simulation results of the FL wireless communication area simulated by the simulation unit 206. The determination unit 208 determines the trajectory of the aircraft 100 so that the provision target region 60 is included in the SL wireless communication area 122 and the installation position of the gateway 40 is included in the FL wireless communication area while the aircraft 100 is making a circular flight, for example.

[0149] The determination unit 208 determines the position of the center of the circular orbit of the aircraft 100, for example, so that the provision target area 60 is included in the SL wireless communication area 122 and the installation position of the gateway 40 is included in the FL wireless communication area while the aircraft 100 is flying in a circular orbit. The determination unit 208 determines the flight altitude of the aircraft 100, for example, so that the provision target area 60 is included in the SL wireless communication area 122 and the installation position of the gateway 40 is included in the FL wireless communication area while the aircraft 100 is flying in a circular orbit. The determination unit 208 determines the flight speed of the aircraft 100 and the radius of the circular orbit of the aircraft 100, for example, so that the provision target area 60 is included in the SL wireless communication area 122 and the installation position of the gateway 40 is included in the FL wireless communication area while the aircraft 100 is flying in a circular orbit.

[0150] The control unit 210 controls various functions of the flying object 100. The control unit 210 controls, for example, the flight functions of the flying object 100. The control unit 210 controls, for example, the flight speed of the flying object 100. The control unit 210 controls, for example, the flight altitude of the flying object 100. The control unit 210 controls, for example, the communication functions of the flying object 100.

[0151] The control unit 210 controls various functions of the aircraft 100, for example, by generating various control signals and transmitting the generated control signals to the aircraft 100 via the network 20. The control unit 210 generates, for example, a flight control signal. The control unit 210 generates, for example, a communication control signal.

[0152] The control unit 210 controls the aircraft 100, for example, to fly in a circle along the trajectory of the aircraft 100 determined by the determination unit 208. For example, if the trajectory of the aircraft 100 determined by the determination unit 208 is a circular orbit, the control unit 210 generates various control signals based on the radius of the circular orbit and the position of the center of the circular orbit, and transmits the generated various control signals to the aircraft 100, thereby causing the aircraft 100 to fly in a circle along the circular orbit. If the aircraft 100 is an autonomous aircraft, the control unit 210 may cause the aircraft 100 to fly in a circle along the circular orbit by transmitting to the aircraft 100 radius information indicating the radius of the circular orbit and center position information indicating the position of the center of the circular orbit.

[0153] 15 is an explanatory diagram for explaining an example of the flow of processing in the system 10. Here, the description will be given assuming that the information processing device 200 is in a start state where it is not executing a simulation.

[0154] In step (sometimes abbreviated as S) 102, the simulation unit 206 simulates the SL antenna 120 formed by the SL beam irradiated by the SL antenna 120 while the aircraft 100 is flying in a circle, based on the SL antenna performance information of the SL antenna 120 and the aircraft performance information of the aircraft 100 stored in the storage unit 202. In S104, the acquisition unit 204 acquires disaster information from the disaster information management device 400 as a target area to be provided.

[0155] In S106, the determination unit 208 determines the trajectory of the aircraft 100 based on the disaster area information included in the disaster information acquired by the acquisition unit 204 in S104 and the simulation results of the SL wireless communication area 122 simulated by the simulation unit 206 in S102, so that the disaster area indicated by the disaster area information is included in the SL wireless communication area 122 while the aircraft 100 is circling. In S108, the control unit 210 controls the aircraft 100 to circling along the trajectory of the aircraft 100 determined by the determination unit 208 in S108. In accordance with control by the information processing device 200, the aircraft 100 begins forming the SL wireless communication area 122 by irradiating an SL beam using the SL antenna 120 so as to include the disaster area. Thereafter, the processing of the system 10 ends.

[0156] 16 schematically illustrates an example of the hardware configuration of a computer 1200 functioning as the information processing device 200. A program installed on the computer 1200 can cause the computer 1200 to function as one or more "units" of an apparatus according to the present embodiment, or can cause the computer 1200 to execute operations associated with the apparatus according to the present embodiment or one or more "units," and / or can cause the computer 1200 to execute a process according to the present embodiment or steps of the process. Such a program can be executed by the CPU 1212 to cause the computer 1200 to perform specific operations associated with some or all of the blocks in the flowcharts and block diagrams described herein.

[0157] The computer 1200 according to this embodiment includes a CPU 1212, a RAM 1214, and a graphics controller 1216, which are interconnected by a host controller 1210. The computer 1200 also includes input / output units such as a communications interface 1222, a storage device 1224, a DVD drive 1226, and an IC card drive, which are connected to the host controller 1210 via an input / output controller 1220. The DVD drive 1226 may be a DVD-ROM drive, a DVD-RAM drive, or the like. The storage device 1224 may be a hard disk drive, a solid-state drive, or the like. The computer 1200 also includes a ROM 1230 and legacy input / output units such as a keyboard, which are connected to the input / output controller 1220 via an input / output chip 1240.

[0158] The CPU 1212 operates according to programs stored in the ROM 1230 and the RAM 1214, thereby controlling each unit. The graphics controller 1216 acquires image data generated by the CPU 1212 into a frame buffer or the like provided in the RAM 1214 or into the graphics controller itself, and causes the image data to be displayed on the display device 1218.

[0159] The communication interface 1222 communicates with other electronic devices via a network. The storage device 1224 stores programs and data used by the CPU 1212 in the computer 1200. The DVD drive 1226 reads programs or data from a DVD-ROM 1227 or the like and provides them to the storage device 1224. The IC card drive reads programs and data from an IC card and / or writes programs and data to an IC card.

[0160] The ROM 1230 stores therein a boot program or the like that is executed by the computer 1200 upon activation, and / or programs that depend on the hardware of the computer 1200. The input / output chip 1240 may also connect various input / output units to the input / output controller 1220 via a USB port, a parallel port, a serial port, a keyboard port, a mouse port, etc.

[0161] The programs are provided by a computer-readable storage medium such as a DVD-ROM 1227 or an IC card. The programs are read from the computer-readable storage medium, installed in the storage device 1224, RAM 1214, or ROM 1230, which are also examples of computer-readable storage media, and executed by the CPU 1212. Information processing described in these programs is read by the computer 1200, and causes cooperation between the programs and the various types of hardware resources described above. An apparatus or method may be configured by implementing operations or processing of information in accordance with the use of the computer 1200.

[0162] For example, when communication is performed between the computer 1200 and an external device, the CPU 1212 may execute a communication program loaded into the RAM 1214 and instruct the communication interface 1222 to perform communication processing based on the processing described in the communication program. Under the control of the CPU 1212, the communication interface 1222 reads transmission data stored in a transmission buffer area provided in the RAM 1214, the storage device 1224, the DVD-ROM 1227, or a recording medium such as an IC card, and transmits the read transmission data to the network, or writes reception data received from the network to a reception buffer area or the like provided on the recording medium.

[0163] Furthermore, the CPU 1212 may cause all or a necessary portion of a file or database stored in an external recording medium such as the storage device 1224, the DVD drive 1226 (DVD-ROM 1227), an IC card, etc. to be read into the RAM 1214, and may perform various types of processing on the data on the RAM 1214. The CPU 1212 may then write back the processed data to the external recording medium.

[0164] Various types of information, such as various types of programs, data, tables, and databases, may be stored on the recording medium and may undergo information processing. The CPU 1212 may perform various types of processing on data read from the RAM 1214, including various types of operations, information processing, conditional judgment, conditional branching, unconditional branching, information search / replacement, etc., as described throughout this disclosure and specified by the instruction sequences of the programs, and write the results back to the RAM 1214. The CPU 1212 may also search for information in a file, database, etc. on the recording medium. For example, if multiple entries, each having an attribute value of a first attribute associated with an attribute value of a second attribute, are stored on the recording medium, the CPU 1212 may search for an entry whose attribute value of the first attribute matches a specified condition from among the multiple entries, read the attribute value of the second attribute stored in the entry, and thereby obtain the attribute value of the second attribute associated with the first attribute that satisfies a predetermined condition.

[0165] The above-described programs or software modules may be stored in a computer-readable storage medium on or near the computer 1200. A recording medium such as a hard disk or RAM provided in a server system connected to a dedicated communication network or the Internet can also be used as a computer-readable storage medium, thereby providing the programs to the computer 1200 via the network.

[0166] The blocks in the flowcharts and block diagrams in the present embodiments may represent stages of a process in which an operation is performed or "parts" of an apparatus responsible for performing the operation. Particular stages and "parts" may be implemented by dedicated circuitry, programmable circuitry provided with computer-readable instructions stored on a computer-readable storage medium, and / or a processor provided with computer-readable instructions stored on a computer-readable storage medium. The dedicated circuitry may include digital and / or analog hardware circuits, including integrated circuits (ICs) and / or discrete circuits. The programmable circuitry may include reconfigurable hardware circuits, such as field programmable gate arrays (FPGAs) and programmable logic arrays (PLAs), including AND, OR, XOR, NAND, NOR, and other logical operations, flip-flops, registers, and memory elements.

[0167] A computer-readable medium may include any tangible device capable of storing instructions that are executed by a suitable device, such that the computer-readable medium having instructions stored thereon comprises an article of manufacture containing instructions that can be executed to create means for performing the operations specified in the flowcharts or block diagrams. Examples of computer-readable media may include electronic, magnetic, optical, electromagnetic, and semiconductor storage media. More specific examples of computer-readable media may include floppy disks, diskettes, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), electrically erasable programmable read-only memory (EEPROM), static random access memory (SRAM), compact disc read-only memory (CD-ROM), digital versatile disc (DVD), Blu-ray disc, memory stick, integrated circuit card, and the like.

[0168] The computer readable instructions may include either assembler instructions, instruction set architecture (ISA) instructions, machine instructions, machine-dependent instructions, microcode, firmware instructions, state-setting data, or source or object code written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Smalltalk®, JAVA®, C++, etc., and conventional procedural programming languages ​​such as the “C” programming language or similar programming languages.

[0169] The computer-readable instructions may be provided to a processor or programmable circuit of a programmable data processing device, such as a computer, locally or via a wide area network (WAN) such as a local area network (LAN) or the Internet, and the computer-readable instructions may be executed to create means for performing the operations specified in the flowcharts or block diagrams. Here, the computer may be a personal computer (PC), a tablet computer, a smartphone, a workstation, a server computer, a general-purpose computer, a special-purpose computer, or the like, or may be a computer system in which multiple computers are connected. Such a computer system in which multiple computers are connected is also called a distributed computing system, and is a broad definition of computer. In a distributed computing system, the multiple computers collectively execute a program by each executing a portion of the program and passing data between the computers as needed during program execution.

[0170] Examples of processors include a computer processor, a central processing unit (CPU), a processing unit, a microprocessor, a digital signal processor, a controller, a microcontroller, etc. A computer may have one or more processors. In a multiprocessor system with multiple processors, each processor executes a portion of a program and passes data between processors as needed during program execution, allowing the multiple processors to collectively execute the program. For example, in multitasking, each of the multiple processors may execute a portion of each task in small chunks by switching tasks at time slice intervals. In this case, which portion of a program each processor executes changes dynamically. Which portion of a program each of the multiple processors executes may also be statically determined by multiprocessor-aware programming.

[0171] Although the present invention has been described above using embodiments, the technical scope of the present invention is not limited to the scope described in the above embodiments. It will be apparent to those skilled in the art that various modifications and improvements can be made to the above embodiments. It is clear from the claims that such modifications and improvements can also be included within the technical scope of the present invention.

[0172] It should be noted that the execution order of each process, such as operations, procedures, steps, and stages, in the devices, systems, programs, and methods shown in the claims, specifications, and drawings is not specifically stated as "before," "prior to," etc., and that the processes can be performed in any order unless the output of a previous process is used in a later process. Even if the operational flow in the claims, specifications, and drawings is described using "first," "next," etc. for convenience, this does not mean that the processes must be performed in this order. [Explanation of symbols]

[0173] 10 system, 20 network, 40 gateway, 60 target area, 100 aircraft, 120 SL antenna, 122 SL wireless communication area, 124 footprint, 126 footprint, 140 FL antenna, 150 trajectory, 200 information processing device, 202 storage unit, 204 acquisition unit, 206 simulation unit, 208 determination unit, 210 control unit, 300 communication terminal, 400 disaster information management device, 1200 computer, 1210 host controller, 1212 CPU, 1214 RAM, 1216 graphic controller, 1218 display device, 1220 input / output controller, 1222 communication interface, 1224 storage device, 1226 DVD drive, 1227 DVD-ROM, 1230 ROM, 1240 input / output chip

Claims

1. a storage unit for storing SL (Service Link) antenna performance information indicating the performance of a SL antenna, which is a collinear antenna, and aircraft performance information indicating the performance of an aircraft equipped with the SL antenna so that horizontally polarized waves are omnidirectional; an acquisition unit that acquires provision area information indicating a provision area of ​​the wireless communication service provided by the aircraft; a simulation unit that simulates an SL wireless communication area formed by an SL beam irradiated by the SL antenna while the aircraft is flying in a circular motion, based on the SL antenna performance information and the aircraft performance information; a determination unit that determines a trajectory of the aircraft based on the provision target area information and a simulation result of the simulation unit simulating the SL wireless communication area so that the provision target area is included in the SL wireless communication area while the aircraft is flying in a circular motion; An information processing device comprising:

2. the simulation unit simulates the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit, the determination unit determines the position of the center of the circular orbit of the aircraft so that the provision target area is included in the SL wireless communication area while the aircraft is flying in a circular orbit. The information processing device according to claim 1 .

3. the storage unit stores the SL antenna performance information including SL antenna gain information indicating an antenna gain of the SL antenna; the simulation unit derives inner and outer diameters of a footprint of the SL wireless communication area based on the SL antenna gain information, thereby simulating the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit. The information processing device according to claim 2 .

4. the simulation unit simulates the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit when the aircraft is at each of a plurality of flight altitudes; the determination unit determines a flight altitude of the aircraft so that the provision target area is included in the SL wireless communication area while the aircraft is flying in a circular orbit. The information processing device according to claim 2 .

5. the storage unit stores the aircraft performance information including minimum flight speed information indicating a minimum flight speed of the aircraft when it is flying in a turn, and allowable bank angle information indicating a allowable bank angle of the aircraft when it is flying in a turn, the simulation unit, when the flight speed of the aircraft is at each of a plurality of flight speeds equal to or greater than the minimum flight speed indicated by the minimum flight speed information, derives a radius of the circular orbit of the aircraft when the bank angle of the aircraft is smaller than the permissible bank angle indicated by the permissible bank angle information, thereby simulating the SL wireless communication area formed by the SL beam while the aircraft is flying in a circular orbit when the flight speed of the aircraft is at each of the flight speeds; the determination unit determines a flight speed of the aircraft and a radius of the circular orbit of the aircraft so that the provision target area is included in the SL wireless communication area while the aircraft is flying in a circular orbit. The information processing device according to claim 2 .

6. The acquisition unit acquires the provision target area information indicating the provision target areas at two different locations, The determination unit determines a trajectory of the aircraft so that the two provision target areas at different positions are included in the SL wireless communication area while the aircraft is flying in a circle. The information processing device according to claim 1 .

7. The storage unit further stores FL (Feeder Link) antenna performance information indicating the performance of an FL antenna, which is a collinear antenna, and installation location information indicating the installation location of a gateway installed on the ground, the simulation unit further simulates an FL wireless communication area formed by an FL beam irradiated by the FL antenna while the aircraft equipped with the FL antenna is flying in a circle so that horizontally polarized waves are omnidirectional, based on the FL antenna performance information and the aircraft performance information; the determination unit determines a trajectory of the aircraft so that the provision target area is included in the SL wireless communication area and the installation position of the gateway is included in the FL wireless communication area while the aircraft is flying in a circle, based on the installation location information and a simulation result of the FL wireless communication area simulated by the simulation unit. The information processing device according to claim 1 .

8. a control unit that controls the flying object so that the flying object makes a turning flight along the trajectory determined by the determination unit; The information processing device according to claim 1 , further comprising:

9. The information processing device according to claim 1 , wherein the acquisition unit acquires the provision target area information indicating the provision target area that is a disaster-affected area that has been affected by a disaster.

10. A program that, when executed by a computer, causes the computer to function as the information processing device according to any one of claims 1 to 5.

11. The information processing device according to any one of claims 1 to 5; the flying vehicle; An information processing system comprising:

12. 1. A computer-implemented information processing method, comprising: an acquisition step of acquiring target area information indicating a target area for providing wireless communication services provided by an aircraft equipped with a collinear SL antenna so that horizontally polarized waves of the SL antenna are omnidirectional; a simulation step of simulating an SL wireless communication area formed by an SL beam irradiated by the SL antenna while the aircraft is flying in a circle, based on SL antenna performance information indicating the performance of the SL antenna and aircraft performance information indicating the performance of the aircraft, both stored in the computer; a determination step of determining a trajectory of the aircraft based on the provision target area information and a simulation result of simulating the SL wireless communication area in the simulation step, so that the provision target area is included in the SL wireless communication area while the aircraft is flying in a circular flight; An information processing method comprising:

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