JP7319117B2 - Guidance system, aircraft carrier, control device, program, and control method - Google Patents

Description

The present invention relates to a guidance system, an aircraft carrier, a management device, a program, and a management method.

An ILS (Instrument Landing System) that guides an aircraft to a runway has been known (see, for example, Patent Document 1).
[Prior art documents]
[Patent Literature]
[Patent Document 1] JP 2012-182509 A

It would be desirable to provide techniques for efficiently assisting an air vehicle to land on a runway from multiple directions.

According to a first aspect of the invention, a guidance system is provided. The guidance system includes a first radio wave transmission unit that transmits a guidance radio wave that is a guidance radio wave for guiding an aircraft and that has directivity in a first azimuth, and a second azimuth opposite to the first azimuth. A first radio wave transmitter having a second radio wave transmitter for transmitting an inductive radio wave having directivity may be provided. The guidance system includes a third radio wave transmission unit that transmits guidance radio waves for a flying object having directivity in a third direction that is substantially the same as the first direction, and a fourth direction that is substantially the same as the second direction. and a second radio wave transmitter having a fourth radio wave transmitter that transmits an inductive radio wave having a property.

The second radio wave transmitter may be arranged in the second azimuth with respect to the position of the first radio wave transmitter. The guided radio wave emitted by the second radio wave transmitter may pass through the center of the runway of the aircraft. The guided radio wave emitted by the third radio wave transmitter may pass through the center of the runway.

The first radio wave transmitter and the second radio wave transmitter may be arranged on a circular runway, and the second radio wave transmitter is oriented in the second direction with respect to the position of the first radio wave transmitter. The induced radio wave transmitted by the second radio wave transmitting unit may pass through the center of the circular runway, and the induced radio wave transmitted by the third radio wave transmitting unit may pass through the circular runway. You can pass through the center. The first radio wave transmitter and the second radio wave transmitter may be arranged on the circumference of the circular runway.

The guidance system may comprise a movement control unit for moving the first radio transmitter and the second radio transmitter along the circumference of the circular runway. The guidance system may include a landing route determining unit that determines a straight landing route passing through the center of the circular runway for the aircraft, and the movement control unit determines the second landing route based on the landing route. Each of the first radio wave transmitter and the second radio wave transmitter may be moved. The landing route determination unit may determine the landing route of a straight line passing through the center of the circular runway along the landing direction of the aircraft. The movement control unit may move each of the first radio wave transmitter and the second radio wave transmitter to each intersection of the landing route and the circumference of the circular runway.

The guidance system includes a fifth radio wave transmission unit that transmits a guidance radio wave having directivity in a fifth direction, and a fifth radio wave transmission unit that transmits a guidance radio wave having directivity in a sixth direction opposite to the fifth direction. a third radio wave transmitter having 6 radio wave transmitters; a seventh radio wave transmitter for transmitting guided radio waves of an aircraft having directivity in a seventh direction substantially identical to the fifth direction; A fourth radio wave transmitter having an eighth radio wave transmitter that transmits an inductive radio wave having directivity in an eighth azimuth that is substantially the same as the azimuth, a landing route determination unit that determines the landing route of the aircraft, Based on the landing route, the combination of the first radio wave transmission unit and the third radio wave transmission unit, the combination of the second radio wave transmission unit and the fourth radio wave transmission unit, the fifth radio wave transmission unit and the seventh radio wave a selection unit for selecting a combination of transmission units or a combination of the sixth radio wave transmission unit and the eighth radio transmission unit; A transmission control unit for transmitting radio waves may be provided.

According to a second aspect of the invention, there is provided an aircraft carrier comprising the stowable and deployable circular runway and the guidance system.

According to a third aspect of the invention, a management device is provided. The management device may comprise a landing route determination unit that determines the landing route of the aircraft. The management device includes a first radio wave transmission unit that transmits a guidance radio wave that is a guidance radio wave for guiding the flying object and that has directivity in a first direction based on the landing route, and a A first radio wave transmitter having a second radio wave transmitter that transmits an inductive radio wave having directivity in a second direction, and an aircraft having directivity in a third direction substantially the same as the first direction Induction by a second radio wave transmitter having a third radio wave transmitting unit that transmits an inductive radio wave and a fourth radio wave transmitting unit that transmits an inductive radio wave having directivity in a fourth direction that is substantially the same as the second direction A transmission control unit for controlling transmission of radio waves may be provided.

According to a fourth aspect of the present invention, there is provided a program for causing a computer to function as the management device.

It should be noted that the above summary of the invention does not list all the necessary features of the invention. Subcombinations of these feature groups can also be inventions.

An example guidance system 100 is shown schematically. An example guidance system 100 is shown schematically. An example of an aircraft 400 is shown schematically. An example of the functional configuration of the management device 300 is shown schematically. An example of the flow of processing by the management device 300 is shown schematically. An example of the flow of processing by the management device 300 is shown schematically. An example aircraft carrier 600 is shown schematically. An example aircraft carrier 600 is shown schematically. An example aircraft carrier 600 is shown schematically. 1 schematically shows an example of a hardware configuration of a computer 1200 functioning as a management device 300. FIG.

Hereinafter, the present invention will be described through embodiments of the invention, but the following embodiments do not limit the invention according to the claims. Also, not all combinations of features described in the embodiments are essential for the solution of the invention.

FIG. 1 schematically shows an example guidance system 100 . Guidance system 100 guides the landing of the aircraft relative to the runway. FIG. 1 shows a circular runway 10 as an example of a runway. Circular runway 10 is located, for example, at any suitable location on land. FIG. 1 also illustrates an air vehicle 400 that functions as a stratospheric platform as an example of an air vehicle.

The guidance system 100 includes multiple radio wave transmitters 200 and a management device 300 . In the example shown in FIG. 1, eight radio wave transmitters 200 are arranged on the circumference of the circular runway 10 . The number of radio wave transmitters 200 to be arranged is not limited to this. For example, the guidance system 100 may include dozens of radio wave transmitters 200 . The radio wave transmitters 200 are preferably arranged at equal intervals on the circumference of the circular runway 10, but may be arranged at irregular intervals. In addition, the radio wave transmitter 200 may be arranged inside the circumference of the circular runway 10 .

Two radio wave transmitters 200 are arranged in pairs. In the example shown in FIG. 1, a pair of two radio transmitters 200 are positioned at each intersection of the diameter and circumference of the circular runway 10 . For example, the radio wave transmitter 200 placed at the point 31 and the radio wave transmitter 200 placed at the point 35 are paired. Also, the radio wave transmitter 200 placed at the point 32 and the radio wave transmitter 200 placed at the point 36 are paired. Also, the radio wave transmitter 200 placed at the point 33 and the radio wave transmitter 200 placed at the point 37 are a pair. Also, the radio wave transmitter 200 placed at the point 34 and the radio wave transmitter 200 placed at the point 38 are a pair.

The radio wave transmitter 200 includes a radio wave transmitter 210 that transmits an inductive radio wave having directivity in a first direction, and a radio wave transmitter that transmits an inductive radio wave having directivity in a second direction opposite to the first direction. 220 . In the example shown in FIG. 1 , the radio wave transmitting unit 210 transmits an inductive radio wave having directivity in the outward direction along the normal line of the circular runway 10, and the radio wave transmitting unit 220 It emits directional radio waves with directivity.

One of the paired two radio wave transmitters 200 includes a radio wave transmitter 210 that transmits an inductive radio wave having directivity in a first direction, and a second direction that is opposite to the first direction. A radio wave transmitting unit 220 that transmits an induced radio wave having directivity in an azimuth, and the other radio wave transmitter 200 transmits an induced radio wave having directivity in a third azimuth that is substantially the same as the first azimuth. and a radio wave transmitting unit 220 that transmits an inductive radio wave having directivity in a fourth azimuth that is substantially the same as the second azimuth.

The management device 300 manages the plurality of radio wave transmitters 200 . The management device 300 uses the radio wave transmission unit 210 of the first radio wave transmitter 200 of the two paired radio wave transmitters 200 and the radio wave transmission unit 220 of the second radio wave transmitter 200 to operate the aircraft. You may manage to guide 400 landings. For example, the management device 300 causes the radio wave transmission unit 210 to transmit an outward guidance radio wave having directivity in the first direction, and causes the radio wave transmission unit 220 to transmit in a third direction substantially the same as the first direction. Landing of the flying object 400 is guided by transmitting a guiding radio wave having directivity toward the center.

For example, the flying object 400 first receives an outward guidance radio wave from the radio wave transmitting unit 210 and flies in the direction of the outward guidance radio wave. When the aircraft 400 approaches the circular runway 10, the aircraft 400 receives the center-directed induced radio waves from the radio wave transmitter 220, and flies on a route where the outward induced radio waves and the center-directed induced radio waves overlap. After landing, the flying object 400 glides in the direction of the guided radio waves directed toward the center.

Here, the azimuth that is substantially the same as the first azimuth includes the first azimuth and includes a deviation that is allowed for guiding the flying object 400 . For example, if a deviation of 1 degree is allowed between the first and third azimuths in guiding the flying object 400, the azimuth substantially identical to the first azimuth means ± 1 degree azimuth. The allowable amount of deviation may vary depending on the performance of the radio wave transmitters 200, the distance between two paired radio wave transmitters 200, the size of the circular runway 10, and the like. is set to

In the example shown in FIG. 1, the guidance system 100, for example, guides an aircraft 400 landing from east to west by an outward guiding radio wave from a radio wave transmitting unit 210 placed at a point 31 and an outward guiding radio wave from a point 35. induced by the center-directed induced radio wave from the radio wave transmitting unit 220 . The flying object 400 can be guided through the center of the circular runway 10 by guiding the flying object 400 by the radio wave transmitting unit 210 and the radio wave transmitting unit 220 respectively arranged at the two intersections of the diameter and the circumference, It can make it possible to optimize the runway length.

Further, the guidance system 100, for example, guides the flying object 400 landing from west to east by the outward guiding radio wave from the radio wave transmitting unit 210 placed at the point 35 and the radio wave transmitting unit 220 placed at the point 31. induced by the center-directed radio waves and In this manner, the two radio wave transmitters 200 that form a pair can efficiently guide the landing of the aircraft 400 from two directions.

The guidance system 100 may guide an aircraft 400 landing from north to south or from south to north by the radio transmitter 200 located at point 33 and the radio transmitter 200 located at point 37. . Further, the guidance system 100 guides an aircraft 400 landing from the northwest to the southwest or from the southwest to the northwest by the radio wave transmitter 200 placed at the point 34 and the radio wave transmitter 200 placed at the point 38. you can Further, the guidance system 100 guides an aircraft 400 landing from northwest to southeast or from southeast to northwest by the radio wave transmitter 200 placed at the point 32 and the radio wave transmitter 200 placed at the point 36. you can Thus, the guidance system 100 can guide the landing of the aircraft 400 from eight directions by using the eight radio wave transmitters 200 arranged on the circular runway 10 . By arranging more radio transmitters 200, the guidance system 100 may be able to guide the landing of the aircraft 400 from more directions.

The management device 300 may have a function of selecting a pair of two radio wave transmitters 200 corresponding to the landing direction of the aircraft 400 from a plurality of radio wave transmitters 200 . The management device 300 determines the landing direction of the aircraft 400 based on information detected by the sensor group 320, for example.

The sensor group 320 includes, for example, a camera that captures images of the sky. Moreover, the sensor group 320 includes, for example, a wind speed sensor that measures wind direction and wind speed on the circular runway 10 . The management device 300 determines the upwind direction as the landing direction, for example, based on the wind direction and wind speed output by the wind speed sensor. Then, the management device 300 selects a pair of two radio wave transmitters 200 corresponding to the landing direction, and one of the two selected radio wave transmitters 200 has a radio wave transmitter 210 and the other has a radio wave transmitter. The aircraft 400 is guided to land by causing 220 to emit guidance radio waves.

The induced radio waves transmitted by the radio wave transmission unit 210 and the induced radio waves transmitted by the radio wave transmission unit 220 may have different frequencies. In addition, the induced radio wave emitted by the radio wave transmission unit 210 may have a stronger radio wave intensity than the induced radio wave emitted by the radio wave transmission unit 220 . The guided radio wave emitted by the radio wave transmitter 210 and the guided radio wave emitted by the radio wave transmitter 220 may be any type of guided radio wave capable of guiding the aircraft 400 . For example, the radio wave transmitting unit 210 and the radio wave transmitting unit 220 may transmit inductive radio waves similar to existing ILS. For example, the radio wave transmission unit 210 transmits a guidance radio wave similar to that of the localizer, and the radio wave transmission unit 220 transmits a guidance radio wave similar to that of the glide path. However, the radio wave transmitter 210 and the radio wave transmitter 220 use frequencies different from those of the existing ILS.

FIG. 2 schematically shows an example guidance system 100 . Here, points different from FIG. 1 will be mainly described. The guidance system 100 shown in FIG. 2 includes two radio transmitters 200 , which are movable along the circumference of the circular runway 10 .

Radio transmitter 200 may be movable along the circumference of circular runway 10 by any configuration. For example, the radio wave transmitter 200 is configured to be movable on rails arranged along the circumference of the circular runway 10 . The radio wave transmitter 200 may be movable in any direction, not limited to the direction along the circumference. The movement of the radio wave transmitter 200 may be performed manually, or may be performed automatically by mechanical control or the like under the control of the management device 300 .

The management device 300 may move the two radio wave transmitters 200 according to the landing direction of the aircraft 400 . For example, when the landing direction of the aircraft 400 is from northwest to southwest, the management device 300 moves the radio wave transmitter 200 placed at the point 31 to the point 38, and moves the radio wave transmitter 200 placed at the point 35. to point 34. Thus, by using the movable radio wave transmitter 200, it is possible to guide the landing of the aircraft 400 from any direction.

Although FIG. 2 exemplifies the case where the guidance system 100 includes two radio wave transmitters 200, the guidance system 100 may include three or more radio wave transmitters 200 without being limited to this. In this case, the management device 300 determines the point at which the radio wave transmitters 200 are arranged according to the landing direction of the flying object 400, and moves the two radio wave transmitters 200 that move less with respect to the point. You may guide 400 landings.

FIG. 3 schematically shows an example of an air vehicle 400. As shown in FIG. Aircraft 400 includes main wing section 410 , propeller 412 , pod 414 , wheels 415 , solar panel 416 , elevator 418 , body section 420 , antenna 430 , antenna 432 , and antenna 434 .

Electric power generated by the solar panel 416 is stored in batteries arranged in at least one of the main wing portion 410 and the main body portion 420 . Battery power is supplied to propeller 412 , elevator 418 , body portion 420 , antenna 430 , antenna 432 , and antenna 434 .

Main unit 420 includes a flight control device and a wireless communication device. The flight controller controls flight of the aircraft 400 . The flight controller controls the flight of vehicle 400 by, for example, rotating propeller 412 and changing the angle of elevator 418 .

Antenna 430 receives the induced radio waves emitted by radio wave transmitter 200 . The flight control device controls the landing of the aircraft 400 according to the guided radio waves received by the antenna 430 .

The wireless communication device performs wireless communication using antennas 432 and 434 . Antenna 432 may be a feeder link antenna. Antenna 434 may be an antenna for service links.

The wireless communication device establishes a feeder link with the gateway 42 by beaming the gateway 42 on the ground using the antenna 432 . Also, the wireless communication device forms a wireless communication area 436 on the ground by emitting a beam toward the ground using an antenna 434 and provides wireless communication services to the user terminals 50 within the wireless communication area 436 . Air vehicle 400 flies in the stratosphere and provides wireless communication services to user terminals 50 on the ground. Air vehicle 400 may function as a stratospheric platform.

The user terminal 50 may be any terminal as long as it can communicate with the aircraft 400 . For example, the user terminal 50 is a mobile phone such as a smart phone. The user terminal 50 may be a tablet terminal, a PC (Personal Computer), or the like. The user terminal 50 may be a so-called IoT (Internet of Thing) device. The user terminal 50 can include anything that corresponds to the so-called IoE (Internet of Everything).

The air vehicle 400 provides wireless communication services to the user terminals 50 by, for example, relaying communications between the user terminals 50 and the network 40 on the ground. Network 40 may include a core network provided by a carrier. The core network may conform to any mobile communication system, such as 3G (3rd Generation) communication system, LTE (Long Term Evolution) communication system, 4G (4th Generation) communication system, and 5G (5th Generation) communication system. It conforms to the mobile communication system after the communication system. Network 40 may include the Internet.

The air vehicle 400 establishes feeder links with gateways 42 located at various locations on the ground, for example, and communicates with the network 40 on the ground via the gateways 42 . Also, for example, the aircraft 400 communicates with the network 40 via the communication satellite 80 . In this case, air vehicle 400 has an antenna for communicating with communication satellite 80 .

Air vehicle 400 , for example, transmits data received from user terminals 50 within wireless communication area 436 to network 40 . Further, for example, when receiving data addressed to the user terminal 50 within the wireless communication area 436 via the network 40 , the flying object 400 transmits the data to the user terminal 50 .

Air vehicle 400 may be controlled by flight management device 500 on the ground. The flight management device 500 may control the aircraft 400 via an O&M (Operation and Maintenance) network 70 . The O&M network 70 is different from a service network for providing wireless communication services to the user terminals 50 . Flight management device 500 may communicate with air vehicle 400 via O&M network 70 , satellite communication device 510 capable of wireless communication with communication satellite 80 , and communication satellite 80 . Note that the flight management device 500 may have a function of wirelessly communicating with the communication satellite 80 and communicate with the aircraft 400 via the communication satellite 80 . O&M network 70 may be communicatively connected to network 40 . O&M network 70 may not be communicatively connected to network 40 .

Manager 300 may communicate with flight manager 500 via O&M network 70 . The management device 300 may cooperate with the flight management device 500 to guide the aircraft 400 to land. For example, the flight management device 500 notifies the management device 300 of the landing route of the aircraft 400 on the circular runway 10, and the management device 300 sends the pair of radio transmitters 200 to guide the aircraft 400 according to the landing route. The radio wave transmitting unit 210 on one side and the radio wave transmitting unit 220 on the other side are caused to transmit inductive radio waves.

FIG. 4 schematically shows an example of the functional configuration of the management device 300. As shown in FIG. The management device 300 includes a communication section 302 , a landing route determination section 304 , a selection section 306 , a transmission control section 308 and a movement control section 310 . Note that it is not essential that the management device 300 have all of these.

The communication unit 302 communicates with the sensor group 320 . The communication unit 302 may receive information output by the sensor group 320 . Also, the communication unit 302 communicates with the flight management device 500 via the O&M network 70 . Communication unit 302 may communicate with air vehicle 400 via O&M network 70 and communication satellite 80 . Also, the communication unit 302 may communicate with the aircraft 400 via the network 40 and the gateway 42 .

A landing route determination unit 304 determines a landing route for the aircraft 400 . The landing route determination unit 304 determines the landing route of the aircraft 400 based on information received by the communication unit 302 from the sensor group 320, for example. For example, the landing route determination unit 304 determines the windward direction as the landing direction based on the wind direction and wind speed output to the wind speed sensor, the direction along the landing direction, and the circular runway 10 A route passing through the center 20 is determined as the landing route. Since the horizontally long flying object 400 as shown in FIG. 3 is vulnerable to crosswinds, the landing direction of the flying object 400 can be stabilized by setting the direction toward the windward as the landing direction.

The landing route determination unit 304 may determine the route received by the communication unit 302 from the flight management device 500 as the landing route for the aircraft 400 . The flight management device 500 determines a landing route for the flying object 400 on the circular runway 10 based on, for example, the flight conditions of the flying object 400 and the surrounding conditions of the circular runway 10 , and transmits the route to the management device 300 . Further, the flight management device 500 receives, for example, guided radio waves from the radio wave transmitter 200 on the ground via the aircraft 400, determines the route for the aircraft 400 to land on the circular runway 10 according to the reception conditions, You may transmit to the management apparatus 300. FIG.

The selection unit 306 selects the radio wave transmission unit 210 and the radio wave transmission unit 220 that guide the aircraft 400 from the plurality of radio wave transmitters 200 based on the landing route determined by the landing route determination unit 304 . The selection unit 306 may select one radio wave transmission unit 210 and the other radio wave transmission unit 220 from the two paired radio wave transmitters 200 located on the landing route.

The transmission control unit 308 causes the radio wave transmission unit 210 and the radio wave transmission unit 220 selected by the selection unit 306 to transmit guided radio waves. The transmission control unit 308 causes the radio wave transmitting unit 210 to transmit an outward guided radio wave, and causes the radio wave transmitting unit 220 to transmit a centrally guided radio wave.

The movement control section 310 moves each of the plurality of radio wave transmitters 200 . The movement control unit 310 , for example, moves each of the plurality of radio wave transmitters 200 arranged on the circumference of the circular runway 10 along the circumference of the circular runway 10 .

The movement control section 310 may move the radio wave transmitter 200 based on the landing route determined by the landing route determination section 304 . The movement control unit 310 moves the pair of two radio wave transmitters 200 to each of the two points of intersection between the landing route and the circumference of the circular runway 10, for example. The transmission control unit 308 causes the radio wave transmitting unit 210 of one of the pair of two radio wave transmitters 200 to transmit an outward guided radio wave and the other radio wave transmitting unit 220 to transmit a center-directed guided radio wave. Landing of body 400 may be guided.

The aircraft monitoring unit 312 monitors the status of the aircraft 400 landing on the circular runway 10 . The flying object monitoring unit 312 acquires the captured image of the flying object 400 captured by the camera in the sensor group 320 via the communication unit 302 and uses the captured image to determine the situation of the flying object 400 . For example, the aircraft monitor 312 determines the distance between the circular runway 10 and the aircraft 400 . Note that the sensor group 320 may include a distance sensor, and the flying object monitoring unit 312 may acquire the distance to the flying object 400 output by the distance sensor via the sensor group 320 .

The transmission control unit 308 may control the transmission of guided radio waves by the radio wave transmission unit 210 and the radio wave transmission unit 220 according to the situation of the aircraft 400 . For example, the transmission control unit 308 causes the radio wave transmission unit 210 to transmit an outward guiding radio wave when the landing aircraft 400 approaches the circular runway 10 by a predetermined first distance. Next, the transmission control unit 308 causes the radio wave transmission unit 220 to transmit center-directed guidance radio waves when the flying object 400 approaches the circular runway 10 by a predetermined second distance. Then, the transmission control unit 308 causes the radio wave transmission unit 210 and the radio wave transmission unit 220 to stop transmitting guidance radio waves when the aircraft 400 has completed landing and the aircraft 400 has stopped.

FIG. 5 schematically shows an example of the flow of processing by the management device 300. As shown in FIG. Here, the flow of processing when guiding the landing of one aircraft 400 will be described.

In step (the step may be abbreviated as S) 102 , the landing route determination unit 304 determines the landing route of the aircraft 400 . The landing route determination unit 304 may determine the route received from the flight management device 500 as the landing route, or the communication unit 302 may determine the landing route based on the information received from the sensor group 320 . In S104, the selection unit 306 selects the radio wave transmission unit 210 that transmits outward guidance radio waves and the radio wave transmission unit 220 that transmits center guidance radio waves based on the landing route determined in S102.

In S106, the transmission control unit 308 causes the radio wave transmission unit 210 to start transmitting outward guidance radio waves. In S108, the transmission control unit 308 determines whether or not the distance between the circular runway 10 and the flying object 400 has become equal to or less than a predetermined threshold. If it is determined that it has become equal to or less than the threshold, the process proceeds to S110.

In S110, the transmission control unit 308 causes the radio wave transmission unit 220 to start transmitting center-directed guidance radio waves. In S112, the transmission control unit 308 determines whether or not the aircraft 400 has completed landing. When it is determined that the aircraft has landed, the process proceeds to S11. In S114, the transmission control unit 308 causes the radio wave transmission unit 210 and the radio wave transmission unit 220 to stop transmitting guidance radio waves.

In this way, by selecting the radio wave transmitter 210 and the radio wave transmitter 220 corresponding to the landing route of the flying object 400 from a plurality of radio wave transmitters 200, the flying object 400 can reach the circular runway 10 from any direction. landing can be efficiently guided.

If the radio wave transmitter 200 is movable, the movement control unit 310 may move the radio wave transmitter 210 and the radio wave transmitter 220 after selecting the radio wave transmitter 210 and the radio wave transmitter 220 in S104. .

FIG. 6 schematically shows an example of the flow of processing by the flying object 400. As shown in FIG. Here, the flow of processing when the flying object 400 lands following guidance by the guidance system 100 will be described.

In S<b>202 , the flying object 400 receives the outward guidance radio wave emitted by the radio wave sending section 210 . In S204, the flying object 400 flies in the direction of the outward guiding radio wave.

In S<b>206 , the flying object 400 receives the center-directed guidance radio wave emitted by the radio wave sending unit 220 . In S208, the flying object 400 flies along a route where the outward induced radio waves and the center-directed induced radio waves overlap.

At S<b>210 , the flying object 400 lands on the circular runway 10 . In S212, the flying object 400 glides in the radio wave direction toward the center. Landing of the flying object 400 is completed when the flying object 400 stops gliding.

In the above embodiment, the case where the circular runway 10 is arranged on land was mainly described as an example, but the circular runway 10 is not limited to this, and may be arranged in a coastal area or deployed on the sea. You may For example, the circular runway 10 is arranged on a semi-fixed mega-float installed on the coast. The MegaFloat may be towable and mobile by a tugboat if desired. The mega-float may be moored with anchors. A circular runway 10 may be realized by a method of coalescing block-shaped floats.

Also for example, the circular runway 10 is housed on an aircraft carrier 600 and deployed when in use. Circular runway 10 may, for example, be collapsible and be collapsed to be accommodated on aircraft carrier 600 and unfolded for use. Also, the circular runway 10 may be of a sliding type, for example, and is slidably housed in the aircraft carrier 600 and slidably deployed when in use.

7, 8 and 9 schematically illustrate an example aircraft carrier 600. FIG. 7 is a top view of aircraft carrier 600, FIG. 8 is a front view of aircraft carrier 600, and FIG. 9 is a side view of aircraft carrier 600. FIG.

An aircraft carrier 600 illustrated in FIGS. 7-9 includes a folding circular runway 610 and a guidance system 100 . The plurality of radio transmitters 200 of the guidance system 100 are placed at respective positions on the circular runway 610 after the circular runway 610 is deployed.

When the circular runway 610 is deployed, the floats 612 are also deployed. By arranging the float 612 on the sea surface 60, deflection of the runway surface of the circular runway 10 can be prevented. The aircraft carrier 600 moves freely forward, backward, left and right by various thrusters, etc., and the aircraft carrier 600 has a dynamic fixed point holding ability (DPS) against wind and waves, and an active roll reduction device to suppress rocking. You may prepare. If the aircraft carrier 600 has thruster and DPS maneuverability and the ability to turn the runway direction upwind, the circular runway 10 may have an elliptical shape instead of a perfect circular shape.

Aircraft carrier 600 may include EV 620 and RORO gate 630 . Vehicle 400 that has landed on circular runway 610 may be transported by EV 620 to an onboard hangar. Vehicle 400 may also be transportable in and out of onboard hangars via RORO gates 630 .

FIG. 10 schematically shows an example of the hardware configuration of a computer 1200 functioning as the management device 300. As shown in FIG. Programs installed on the computer 1200 cause the computer 1200 to function as one or more "parts" of the apparatus of the present embodiments, or cause the computer 1200 to operate or perform operations associated with the apparatus of the present invention. Multiple "units" can be executed and/or the computer 1200 can be caused to execute the process or steps of the process according to the present invention. Such programs may be executed by CPU 1212 to cause computer 1200 to perform certain operations associated with some or all of the blocks in the flowcharts and block diagrams described herein.

Computer 1200 according to this embodiment includes CPU 1212 , RAM 1214 , and graphics controller 1216 , which are interconnected by host controller 1210 . Computer 1200 also includes input/output units such as communication interface 1222 , storage device 1224 , and IC card drives, which are connected to host controller 1210 via input/output controller 1220 . Storage devices 1224 may be hard disk drives, solid state drives, and the like. Computer 1200 also includes legacy input/output units, such as ROM 1230 and keyboard, which are connected to input/output controller 1220 via input/output chip 1240 .

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

Communication interface 1222 communicates with other electronic devices over a network. Storage device 1224 stores programs and data used by CPU 1212 within computer 1200 . The IC card drive reads programs and data from IC cards and/or writes programs and data to IC cards.

ROM 1230 stores therein programs that are dependent on the hardware of computer 1200, such as a boot program that is executed by computer 1200 upon activation. Input/output chip 1240 may also connect various input/output units to input/output controller 1220 via USB ports, parallel ports, serial ports, keyboard ports, mouse ports, and the like.

A program is provided by a computer-readable storage medium such as an IC card. The program is read from a computer-readable storage medium, installed in storage device 1224 , RAM 1214 , or ROM 1230 , which are also examples of computer-readable storage media, and executed by CPU 1212 . The information processing described within these programs is read by computer 1200 to provide coordination between the programs and the various types of hardware resources described above. An apparatus or method may be configured by implementing information operations or processing according to the use of computer 1200 .

For example, when communication is performed between the computer 1200 and an external device, the CPU 1212 executes a communication program loaded into the RAM 1214 and sends communication processing to the communication interface 1222 based on the processing described in the communication program. you can command. Under the control of the CPU 1212, the communication interface 1222 reads the transmission data stored in the transmission buffer area provided in the RAM 1214, the storage device 1224, or a recording medium such as an IC card, and transmits the read transmission data to the network. Received data transmitted or received from a network is written in a receive buffer area or the like provided on a recording medium.

The CPU 1212 also causes the RAM 1214 to read all or necessary portions of files or databases stored in an external recording medium such as a storage device 1224 or an IC card, and performs various types of processing on the data on the RAM 1214. may be executed. CPU 1212 may then write back the processed data to an external recording medium.

Various types of information, such as various types of programs, data, tables, and databases, may be stored on recording media and subjected to information processing. CPU 1212 performs various types of operations on data read from RAM 1214, information processing, conditional decisions, conditional branching, unconditional branching, and information retrieval, which are described throughout this disclosure and are specified by instruction sequences of programs. Various types of processing may be performed, including /replace, etc., and the results written back to RAM 1214 . In addition, the CPU 1212 may search for information in a file in a recording medium, a database, or the like. For example, when a plurality of entries each having an attribute value of a first attribute associated with an attribute value of a second attribute are stored in the recording medium, the CPU 1212 selects the first attribute from among the plurality of entries. search for an entry that matches the specified condition of the attribute value of the attribute, read the attribute value of the second attribute stored in the entry, and thereby determine the first attribute that satisfies the predetermined condition An attribute value of the associated second attribute may be obtained.

The programs or software modules described above may be stored in a computer-readable storage medium on or near computer 1200 . Also, 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 be used as a computer-readable storage medium, whereby the program can be transferred to the computer 1200 via the network. offer.

The blocks in the flowcharts and block diagrams in this embodiment may represent steps in the process in which the operations are performed or "parts" of the apparatus responsible for performing the operations. Certain steps and "sections" may be provided with dedicated circuitry, programmable circuitry provided with computer readable instructions stored on a computer readable storage medium, and/or computer readable instructions provided with computer readable instructions stored on a computer readable storage medium. It may be implemented by a processor. Dedicated circuitry may include digital and/or analog hardware circuitry, and may include integrated circuits (ICs) and/or discrete circuitry. Programmable circuits, such as Field Programmable Gate Arrays (FPGAs), Programmable Logic Arrays (PLAs), etc., perform AND, OR, EXCLUSIVE OR, NOT AND, NOT OR, and other logical operations. , flip-flops, registers, and memory elements.

A computer-readable storage medium may comprise any tangible device capable of storing instructions to be executed by a suitable device, such that a computer-readable storage medium having instructions stored thereon may be illustrated in flowchart or block diagram form. It will comprise an article of manufacture containing instructions that can be executed to create means for performing specified operations. Examples of computer-readable storage media may include electronic storage media, magnetic storage media, optical storage media, electromagnetic storage media, semiconductor storage media, and the like. More specific examples of computer readable storage media 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 cards, and the like.

The computer readable instructions may be assembler instructions, Instruction Set Architecture (ISA) instructions, machine instructions, machine dependent instructions, microcode, firmware instructions, state setting data, or object oriented programming such as Smalltalk, JAVA, C++, etc. language, and any combination of one or more programming languages, including conventional procedural programming languages, such as the "C" programming language or similar programming languages. good.

Computer readable instructions are used to produce means for a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus, or programmable circuits to perform the operations specified in the flowchart or block diagrams. A general purpose computer, special purpose computer, or other programmable data processor, locally or over a wide area network (WAN) such as the Internet, etc., to execute such computer readable instructions. It may be provided in the processor of the device or in a programmable circuit. Examples of processors include computer processors, processing units, microprocessors, digital signal processors, controllers, microcontrollers, and the like.

Although the present invention has been described above using the embodiments, the technical scope of the present invention is not limited to the scope described in the above embodiments. It is obvious to those skilled in the art that various modifications and improvements can be made to the above embodiments. It is clear from the description of the scope of claims that forms with such modifications or improvements can also be included in the technical scope of the present invention.

The execution order of each process such as actions, procedures, steps, and stages in the devices, systems, programs, and methods shown in the claims, the specification, and the drawings is particularly "before", "before etc., and it should be noted that they can be implemented in any order unless the output of the previous process is used in the subsequent process. Regarding the operation flow in the claims, the specification, and the drawings, even if the description is made using "first," "next," etc. for convenience, it means that it is essential to carry out in this order. not a thing

10 circular runway, 20 centers, 31, 32, 33, 34, 35, 36, 37, 38 points, 40 networks, 42 gateways, 50 user terminals, 60 sea level, 70 O&M networks, 80 communication satellites, 100 guidance systems, 200 radio wave transmitter, 210 radio wave transmitter, 220 radio wave transmitter, 300 management device, 302 communication unit, 304 landing route determination unit, 306 selector, 308 transmission control unit, 310 movement control unit, 312 aircraft monitoring unit, 320 Sensor group, 400 aircraft, 410 main wing, 412 propeller, 414 pod, 415 wheel, 416 solar panel, 418 elevator, 420 main body, 430 antenna, 432 antenna, 434 antenna, 436 wireless communication area, 500 flight management device , 510 satellite communication device, 600 aircraft carrier, 610 circular runway, 612 float, 620 EV, 630 RORO gate, 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, 1230 ROM, 1240 input/output chip

Claims (11)

A first radio wave transmitter for transmitting a guided radio wave for guiding an aircraft and having directivity in a first direction, and a directivity in a second direction opposite to the first direction. a first radio wave transmitter having a second radio wave transmitter that transmits a guided radio wave that passes through the center of the circular runway of the aircraft;
a third radio wave transmitting unit that has directivity in a third direction substantially identical to the first direction and transmits guidance radio waves for an aircraft passing through the center of the circular runway; and the second direction. a fourth radio wave transmitter that transmits an induction radio wave having directivity in a substantially identical fourth azimuth; a radio transmitter,
a landing route determination unit that determines the landing route of the flying object;
a selection unit that selects a combination of the first radio wave transmission unit and the third radio wave transmission unit or a combination of the second radio wave transmission unit and the fourth radio wave transmission unit based on the landing route;
when the combination of the first radio wave transmission unit and the third radio wave transmission unit is selected by the selection unit, the first radio wave transmission unit is caused to transmit an inductive radio wave in the first direction, and the third radio wave transmission is performed. section to transmit an inductive radio wave in the third direction, and when the combination of the second radio wave transmission section and the fourth radio wave transmission section is selected by the selection section, the fourth radio wave transmission section transmits the fourth radio wave transmission section. a transmission control unit that causes the second radio wave transmission unit to transmit an inductive radio wave in the direction of
The first radio transmitter and the second radio transmitter are arranged at respective intersections of the diameter and circumference of the circular runway,
The transmission control unit determines in advance the flying object landing on the circular runway from the circular runway when the combination of the first radio wave transmission unit and the third radio wave transmission unit is selected by the selection unit. When the flying object approaches the first distance set, the first radio wave transmitting unit is caused to transmit a guided radio wave in the first direction, and the flying object moves from the circular runway to a distance shorter than the first distance. 2, the flying object is caused to pass through the center of the circular runway by causing the third radio wave transmitting unit to transmit guided radio waves in the third direction, and the flying object starts to run. A guidance system for stopping the transmission of guidance radio waves by the first radio wave transmission section and the third radio wave transmission section in response to completion of the flying object and the stopping of the aircraft. The landing route determination unit determines a windward direction as a landing direction based on the wind direction and wind speed output by a wind speed sensor that measures the wind direction and wind speed on the circular runway, and determines a direction along the landing direction. and determining a landing route as a route passing through the center of the circular runway. The guidance system according to claim 1 or 2 , further comprising a movement control unit that moves the first radio wave transmitter and the second radio wave transmitter along the circumference of the circular runway. The landing route determination unit determines a straight landing route passing through the center of the circular runway for the aircraft,
The guidance system according to claim 3 , wherein the movement control unit moves each of the first radio wave transmitter and the second radio wave transmitter based on the landing route. 5. The guidance system according to claim 4 , wherein the landing route determining unit determines the landing route of a straight line passing through the center of the circular runway along the landing direction of the aircraft. 6. The movement control unit according to claim 4 , wherein the movement control unit moves each of the first radio wave transmitter and the second radio wave transmitter to each intersection of the landing route and the circumference of the circular runway. guidance system. a fifth radio wave transmitting section for transmitting an induced radio wave having directivity in a fifth azimuth; and a sixth radio wave transmitting section for transmitting an induced radio wave having directivity in a sixth azimuth opposite to the fifth azimuth. a third radio wave transmitter having
a seventh radio wave transmitting section for transmitting guidance radio waves of an aircraft having directivity in a seventh direction substantially the same as the fifth direction; a fourth radio wave transmitter having an eighth radio wave transmitter that transmits an inductive radio wave having
with
The selection unit, based on the landing route, combines the first radio wave transmission unit and the third radio wave transmission unit, the combination of the second radio wave transmission unit and the fourth radio wave transmission unit, and the fifth radio wave transmission unit. and the combination of the seventh radio wave transmission unit, or the combination of the sixth radio wave transmission unit and the eighth radio wave transmission unit,
The transmission control unit causes the fifth radio wave transmission unit to transmit an inductive radio wave in the fifth direction when the combination of the fifth radio wave transmission unit and the seventh radio wave transmission unit is selected by the selection unit. , causing the seventh radio wave transmission unit to transmit an inductive radio wave in the seventh azimuth, and when the selection unit selects a combination of the sixth radio wave transmission unit and the eighth radio wave transmission unit, the sixth radio wave causing the transmitting unit to transmit an induced radio wave in the sixth direction, and causing the eighth radio wave transmitting unit to transmit an induced radio wave in the eighth direction;
3. Guidance system according to claim 1 or 2 . the stowable and deployable circular runway;
An aircraft carrier comprising a guidance system according to any one of claims 1 to 7 . a landing route determination unit that determines the landing route of the flying object;
A first radio wave transmitter for transmitting a guided radio wave for guiding an aircraft and having directivity in a first direction, and a directivity in a second direction opposite to the first direction. a first radio wave transmitter having a second radio wave transmitter that transmits a guided radio wave that passes through the center of the circular runway of the flying object; A third radio wave transmitting unit that has directivity and transmits a guidance radio wave for an aircraft passing through the center of the circular runway; and a guidance radio wave that has directivity in a fourth direction that is substantially the same as the second direction. and a fourth radio wave transmitter that transmits the second radio wave transmitter arranged in the second direction with respect to the position of the first radio wave transmitter, based on the landing route, the second radio wave transmitter a selection unit that selects a combination of one radio wave transmission unit and the third radio wave transmission unit, or a combination of the second radio wave transmission unit and the fourth radio wave transmission unit;
when the combination of the first radio wave transmission unit and the third radio wave transmission unit is selected by the selection unit, the first radio wave transmission unit is caused to transmit an inductive radio wave in the first direction, and the third radio wave transmission is performed. section to transmit an inductive radio wave in the third direction, and when the combination of the second radio wave transmission section and the fourth radio wave transmission section is selected by the selection section, the fourth radio wave transmission section transmits the fourth radio wave transmission section. a transmission control unit that causes the second radio wave transmission unit to transmit an inductive radio wave in the direction of
The first radio transmitter and the second radio transmitter are arranged at respective intersections of the diameter and circumference of the circular runway,
The transmission control unit determines in advance the flying object landing on the circular runway from the circular runway when the combination of the first radio wave transmission unit and the third radio wave transmission unit is selected by the selection unit. When the flying object approaches the first distance set, the first radio wave transmitting unit is caused to transmit a guided radio wave in the first direction, and the flying object moves from the circular runway to a distance shorter than the first distance. 2, the flying object is caused to pass through the center of the circular runway by causing the third radio wave transmitting unit to transmit guided radio waves in the third direction, and the flying object starts to run. A management device for stopping transmission of induction radio waves by the first radio wave transmission section and the third radio wave transmission section in response to completion of the flight object and the suspension of the flying object. A program for causing a computer to function as the management device according to claim 9 . a landing route determination step of determining the landing route of the aircraft;
A first radio wave transmitter for transmitting a guided radio wave for guiding an aircraft and having directivity in a first direction, and a directivity in a second direction opposite to the first direction. a first radio wave transmitter having a second radio wave transmitter that transmits a guided radio wave that passes through the center of the circular runway of the flying object; A third radio wave transmitting unit that has directivity and transmits a guidance radio wave for an aircraft passing through the center of the circular runway; and a guidance radio wave that has directivity in a fourth direction that is substantially the same as the second direction. and a fourth radio wave transmitter that transmits the second radio wave transmitter arranged in the second direction with respect to the position of the first radio wave transmitter, based on the landing route, the second radio wave transmitter a selection step of selecting a combination of one radio wave transmission unit and the third radio wave transmission unit or a combination of the second radio wave transmission unit and the fourth radio wave transmission unit;
When the combination of the first radio wave transmitter and the third radio wave transmitter is selected in the selection step, the first radio wave transmitter is caused to transmit an inductive radio wave in the first direction, and the third radio wave is transmitted. section to transmit an induction radio wave in the third direction, and when the combination of the second radio wave transmission section and the fourth radio wave transmission section is selected in the selection step, the fourth radio wave transmission section transmits the fourth radio wave transmission section. and a transmission control step of causing the second radio wave transmitting unit to transmit the guided radio wave in the second direction ,
The first radio transmitter and the second radio transmitter are arranged at respective intersections of the diameter and circumference of the circular runway,
In the transmission control step, when the combination of the first radio wave transmitter and the third radio wave transmitter is selected in the selection step, the flying object landing on the circular runway is predetermined from the circular runway. When the flying object approaches the first distance set, the first radio wave transmitting unit is caused to transmit a guided radio wave in the first direction, and the flying object moves from the circular runway to a distance shorter than the first distance. 2, the flying object is caused to pass through the center of the circular runway by causing the third radio wave transmitting unit to transmit guided radio waves in the third direction, and the flying object starts to run. A management method for stopping the transmission of induction radio waves by the first radio wave transmission section and the third radio wave transmission section in response to completion of the flying object and the suspension of the flying object.

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