JP2023109270A - Operation method of flight frame, operation method of aerial taking off and landing system, and flight frame - Google Patents

Abstract

To provide an operation method of a flight frame which enables even an aircraft, such as a jet plane, to accelerate a flight frame to a usable high speed range, and to provide an operation method of an aerial taking-off and landing system and the flight frame.SOLUTION: A flight frame 20 has a frame body provided with a mounting surface on which an air vehicle 10 may be placed, and multiple electric fans housed in the frame body. In an operation method of the flight frame 20, the flight frame 20 is lifted up and then fallen in the air and concurrently a velocity component generated by the falling is converted into a velocity component in a travel direction.SELECTED DRAWING: Figure 6

Description

TECHNICAL FIELD The present disclosure relates to a method of operating a flight platform, a method of operating an air takeoff and landing system, and a flight platform.

Fixed-wing aircraft are suitable for long-distance transport, but they require a runway for take-off and landing, which limits their available locations. In particular, in places such as urban centers, mountainous areas, and remote islands, it is often difficult to secure space for the construction of runways. be.

Here, for example, in Patent Document 1, a fixed-wing aircraft is coupled to an unmanned helicopter, the unmanned helicopter is raised and accelerated together with the fixed-wing aircraft, and the fixed-wing aircraft is separated from the unmanned helicopter in the sky, so that the runway is Techniques have been disclosed for at least taking off fixed-wing aircraft. Also disclosed is a technique for landing a fixed-wing aircraft without a runway by connecting an unmanned helicopter to the fixed-wing aircraft in the sky.

JP 2017-30739 A

However, if the target aircraft is a propeller aircraft, it is possible to take off and land at about 100km/h to 200km/h, so taking off and landing using an unmanned helicopter seems realistic, but if the target aircraft is a jet aircraft, it will take off and land at 300km/h. /h or more is required, it is considered difficult to take off and land using an unmanned helicopter. This is not limited to the case of using an unmanned helicopter, but the same concern exists with flight platforms equipped with a large number of electric fans.

Therefore, in order to realize takeoff and landing of a wide variety of aircraft using the flight platform, it is important how to accelerate the flight platform to a high speed range.

The present disclosure has been made in view of such circumstances, and an operating method of a flight platform and an aerial takeoff and landing system capable of accelerating the flight platform to a usable high speed range even for an aircraft such as a jet aircraft. The purpose is to provide a method of operation and a flight platform for

In order to solve the above problems, the flight platform operation method, air takeoff and landing system operation method, and flight platform of the present disclosure employ the following means.
That is, a flight platform operation method according to an aspect of the present disclosure includes a flight platform having a platform body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans housed in the platform body. In the operation method, the flight platform is lifted, and the lifted flight platform is dropped in the air, and the velocity component generated by the drop is converted into the velocity component in the traveling direction.

Further, a method of operating an aerial takeoff and landing system according to an aspect of the present disclosure includes a flight cradle having a cradle body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans accommodated in the cradle body. and the aircraft having a propulsion device, wherein the flight platform is raised while the aircraft is mounted on the mounting surface, and the aircraft is mounted on the mounting surface. While the flight platform is dropped in the air while being mounted, the velocity component generated by the drop is converted into a velocity component in the direction of travel, and when the aircraft has a lift force capable of supporting its own weight, the aircraft is launched into the flight. Launch from the pedestal.

Further, a flight platform according to an aspect of the present disclosure includes a platform body provided with a mounting surface on which an aircraft can be mounted, a plurality of electric fans housed in the platform body, and a platform control device. The control device performs an ascending mode for raising the flight platform, and an acceleration mode for dropping the raised flight platform in the air and converting a velocity component generated by the drop into a velocity component in the traveling direction.

According to the present disclosure, the flight platform can be accelerated to a range of usable high speeds even for aircraft such as jets.

1 is a configuration diagram of an air takeoff and landing system according to an embodiment of the present disclosure; FIG. 1 is a configuration diagram of an aircraft control device, a gantry control device, or a base station control device; FIG. 1 is a plan view of a flight cradle according to an embodiment of the present disclosure; FIG. 1 is a side view of a flight cradle according to an embodiment of the present disclosure; FIG. 1 is a side view of a flight cradle according to an embodiment of the present disclosure; FIG. 1 is a conceptual diagram of a method of operating a flight platform according to an embodiment of the present disclosure (during takeoff); FIG. 1 is a conceptual diagram of a method of operating a flight platform according to an embodiment of the present disclosure (during landing); FIG. FIG. 11 illustrates the pivoting of the flight platform; FIG. 11 illustrates the pivoting of the flight platform; FIG. 4 is a front view showing the bank angle of the aircraft and the bank angle of the flight platform; 1 is a configuration diagram of an air takeoff and landing system according to an embodiment of the present disclosure; FIG. 1 is a configuration diagram of an air takeoff and landing system according to an embodiment of the present disclosure; FIG. 1 is a conceptual diagram according to Example 1 of a method of operating an air takeoff and landing system according to an embodiment of the present disclosure; FIG. FIG. 7 is a conceptual diagram according to Example 2 of the operation method of the air takeoff and landing system according to an embodiment of the present disclosure; FIG. 2 is a side view of a flight platform with cameras installed; 1 is a front view of an aircraft captured by a camera; FIG. 1 is a front view of an aircraft captured by a camera; FIG. FIG. 2 is a side view of a flight platform with a laser range finder installed; 1 is a plan view of a flight platform on which a laser range finder is installed; FIG. FIG. 10 is a side view of the flight platform on which the guidance part is installed (at the time of approach); Fig. 10 is a side view of the flight platform with the guidance part installed (at the time of contact); FIG. 11 is a side view of the flight platform on which the guidance part is installed (when mounted); It is a side view of a guidance part and an accommodation pit. FIG. 4 is a side view showing a state in which the guide portion is housed in the gantry main body; FIG. 11 is a side view of the guidance section provided with a fairing; FIG. 4 is a side view of a guiding portion provided with a through hole; FIG. 11 is a perspective view showing a modified example of the guiding portion; It is the front view which showed the fixing pad which fixes a wheel. It is the front view which showed the fixing pad which fixes a wheel. 1 is a perspective view of a flight platform provided with wings; FIG. FIG. 4 is a perspective view showing a wing frame; FIG. 4 is a perspective view showing a skin material; FIG. 4 is a plan view showing the framework when the wings are extended; FIG. 4 is a plan view showing the framework when the wings are folded; 34 is a partially enlarged view of the A portion shown in FIG. 33; FIG. 36 is a side view of FIG. 35; FIG. FIG. 34 is a partially enlarged view of a B portion shown in FIG. 33; FIG. 38 is a side view of FIG. 37; FIG. 39 is a side view of FIG. 38; FIG. 4 is a perspective view showing how air is introduced between the upper surface and the lower surface of the skin material; FIG. 4 is a side view of a duct that introduces air between the upper surface and the lower surface of the skin material; FIG. 4 is a perspective view showing a skin material provided with wires;

Hereinafter, a method of operating a flight platform, a method of operating an air takeoff and landing system, and a flight platform according to an embodiment of the present disclosure will be described with reference to the drawings.

As shown in FIG. 1, the air takeoff and landing system 1 comprises an aircraft 10, a flight platform 20, and a communication base station 30. As shown in FIG.
Aircraft 10, flight platform 20 and communication base station 30 are capable of communicating with each other. Also, the aircraft 10, the flight platform 20, and the communication base station 30 are each capable of communicating with a satellite positioning system and an external base station.
Hereinafter, configurations of the aircraft 10, the flight platform 20, and the communication base station 30 will be individually described.

[About the configuration of the aircraft]
Aircraft 10 has a propulsion system. The aircraft 10 is free to fly (including takeoff and landing) due to the propulsion system. Examples of propulsion devices include jet engines and electric fans.
Aircraft 10 may be manned or unmanned.

Aircraft 10 has an aircraft controller 100 .
The aircraft control device 100 performs communication with the outside (flight platform 20, communication base station 30, satellite positioning system, etc.), attitude control of the aircraft, sensing, and other processes necessary for the functions of the aircraft 10.

The aircraft control device 100 includes, for example, a CPU (Central Processing Unit: processor) 111, a main memory (main memory) 112, a secondary storage (secondary storage: memory) 113, and the like.

For example, the CPU 111 controls each device of the aircraft 10 by an OS (Operating System) stored in a secondary storage device 113 connected via a bus, and executes various programs stored in the secondary storage device 113. Various processes are executed by executing One or a plurality of CPUs 111 may be provided and cooperate with each other to implement processing.

The main memory device 112 is composed of a writable memory such as a cache memory and a RAM (Random Access Memory), and is used as a work area for reading the execution program of the CPU 111 and writing processing data by the execution program. .

The secondary storage device 113 is a non-transitory computer readable storage medium. The secondary storage device 113 is, for example, a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, a semiconductor memory, or the like. Examples of the secondary storage device 113 include ROM (Read Only Memory), HDD (Hard Disk Drive), SSD (Solid State Drive) flash memory, and the like. The secondary storage device 113 includes, for example, an OS such as Windows (registered trademark), iOS (registered trademark), and Android (registered trademark) for controlling the entire information processing apparatus, BIOS (Basic Input/Output System), peripheral It stores various device drivers, various application software, and various data and files for hardware operation of devices. The secondary storage device 113 also stores programs for implementing various processes and various data required for implementing various processes. A plurality of secondary storage devices 113 may be provided, and the above-described programs and data may be divided and stored in each secondary storage device 113 .

A series of processes for realizing the functions of the aircraft 10 are stored in the secondary storage device 113 or the like in the form of a program, for example. , various functions are realized by executing information processing and arithmetic processing. The program may be provided in a form pre-installed in the secondary storage device 113, stored in another non-temporary computer-readable storage medium, or provided via wired or wireless communication means. A form in which the data is distributed via the Internet may also be applied. Examples of non-transitory computer-readable storage media include magnetic disks, magneto-optical disks, CD-ROMs, DVD-ROMs, semiconductor memories, and the like.

The aircraft control device 100 also includes an external interface 114, a communication interface 115, and the like. These units are connected to each other directly or indirectly via a bus, and cooperate with each other to perform various processes.

The external interface 114 is an interface for connecting with an external device. Examples of external devices include an external monitor, a USB memory, an external HDD, an external camera, and the like. Although only one external interface is shown in the example shown in FIG. 2, a plurality of external interfaces may be provided.

The communication interface 115 functions as an interface for connecting to a network, communicating with other devices, and transmitting and receiving information. The communication interface 115 communicates with other devices, for example, by wire or wirelessly. Examples of wireless communication include communication through lines such as Bluetooth (registered trademark), Wi-Fi, mobile communication systems (3G, 4G, 5G, 6G, LTE, etc.), satellite positioning systems, and wireless LANs. An example of wired communication is communication through a line such as a wired LAN (Local Area Network).

[About the basic configuration of the flight platform]
As shown in FIG. 1 , the flight platform 20 is a device capable of flying with the aircraft 10 mounted on the mounting surface 22 .

As shown in FIG. 3 , the flight cradle 20 includes a cradle body 21 and a plurality of electric fans 23 .

The gantry main body 21 has a frame assembled in a grid pattern, and each frame is rigidly connected to be integrated.
A plurality of electric fans 23 are accommodated in the gantry body 21 .

The electric fan 23 is a device that is driven by an electric motor to generate thrust.
The electric fans 23 are arranged in a grid. By arranging the electric fans 23 in a grid pattern, the electric fans 23 can be arranged densely and efficiently.
The number and arrangement of the electric fans 23 can be appropriately changed according to the specifications of the flight platform 20 and the weight of the aircraft 10 on which it is mounted.

As shown in FIG. 4 , the electric fan 23 accommodated in the gantry body 21 does not protrude from the upper surface of the gantry body 21 .
As a result, the upper surface of the flight platform 20 becomes flat.

As shown in FIG. 1 , a mounting surface 22 on which the aircraft 10 is mounted is provided in the center region of the upper surface of the gantry body 21 . The mounting surface 22 is preferably symmetrical with respect to the center of gravity of the gantry main body 21 .
The lower part of the mounting surface 22 (inside the flight cradle 20) may contain equipment necessary for operating the flight cradle 20 (eg, batteries, cradle control device 200, communication equipment, etc.).

The gantry control device 200 communicates with the outside (aircraft 10, communication base station 30, satellite positioning system, etc.), controls the attitude of the flight gantry 20, controls the rotation speed of the electric fan 23, performs sensing, and performs other functions of the flight gantry 20. It does what it needs to do for the function.
The gantry control device 200 will be described later.

As shown in FIG. 3, the plurality of electric fans 23 constitute a fan unit 24 in which a total of four fans in two rows and two columns form one set.
The fan units 24 include two types of fixed fan units 24A and movable fan units 24B.
The cross-hatching shown in FIG. 3 is drawn so that the fixed fan unit 24A and the movable fan unit 24B can be easily distinguished, and is not an element constituting the flight platform 20. As shown in FIG.

The fixed fan units 24 A are four fan units 24 arranged at the four corners of the flight platform 20 .
On the other hand, the movable fan unit 24B is the fan unit 24 other than the fixed fan unit 24A.

As shown in FIG. 4 , the fixed fan unit 24A and the movable fan unit 24B can send airflow downward to the gantry body 21 . This allows the flight platform 20 to be raised and lowered.

As shown in FIG. 5, each movable fan unit 24B is tiltable in the longitudinal direction with respect to the gantry main body 21, and can send airflow in the rearward-downward direction or the forward-downward direction of the flight cradle 20. As shown in FIG. This allows the flight platform 20 to move forward and backward.

It should be noted that it is not necessary to tilt all the movable fan units 24B in the same direction and by the same angle, and the direction and angle of tilt may be different for each movable fan unit 24B.
Further, it is not always necessary to have a configuration in which each movable fan unit 24B is tilted, and a configuration in which each electric fan 23 is tilted may be adopted.

The fixed fan unit 24A is fixed to the gantry body 21 without tilting like the movable fan unit 24B.
By adjusting the rotational speed of the electric fan 23 of each fixed fan unit 24A, the attitude of the flight platform 20 in the pitch direction or roll direction can be controlled.

The four electric fans 23 constituting one fixed fan unit 24A are arranged so that two electric fans 23 adjacent in the diagonal direction rotate in the same direction at the same number of revolutions and are adjacent in the row direction (column direction). The two electric fans 23 are configured to rotate in different directions.
By adjusting the number of rotations of the electric fans 23 adjacent in the row direction (column direction), the attitude of the flight platform 20 in the yaw direction can be controlled.

As described above, the flight platform 20 controls the rotation speed (output) of the electric fan 23 and the tilt angle of the movable fan unit 24B, thereby allowing the flight platform 20 to move upward, downward, forward and backward, and to move in the pitch direction, roll direction and yaw direction. You can arbitrarily change the direction and attitude. This is the same even when the aircraft 10 is mounted.

Here, control of the rotation speed of each electric fan 23 and the tilt angle of the movable fan unit 24B is executed by the gantry control device 200. FIG.

As shown in FIG. 2, the gantry control device 200 includes, for example, a CPU (Central Processing Unit: processor) 211, a main memory (main memory) 212, a secondary storage (secondary storage: memory) 213, and the like. .

The CPU 211 controls each device of the flight platform 20 by an OS (Operating System) stored in a secondary storage device 213 connected via a bus, for example, and also controls various devices stored in the secondary storage device 213. Various processes are executed by executing the program. One or a plurality of CPUs 211 may be provided and cooperate with each other to implement processing.

The main memory device 212 is composed of a writable memory such as a cache memory and a RAM (Random Access Memory), and is used as a work area for reading the execution program of the CPU 211 and writing processing data by the execution program. .

The secondary storage device 213 is a non-transitory computer readable storage medium. The secondary storage device 213 is, for example, a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, a semiconductor memory, or the like. Examples of the secondary storage device 213 include ROM (Read Only Memory), HDD (Hard Disk Drive), SSD (Solid State Drive) flash memory, and the like. The secondary storage device 213 includes, for example, an OS such as Windows (registered trademark), iOS (registered trademark), and Android (registered trademark) for controlling the entire information processing apparatus, BIOS (Basic Input/Output System), peripheral It stores various device drivers, various application software, and various data and files for hardware operation of devices. The secondary storage device 213 also stores programs for implementing various processes and various data required for implementing various processes. A plurality of secondary storage devices 213 may be provided, and the above-described programs and data may be divided and stored in each secondary storage device 213 .

A series of processes for realizing the functions of the flight platform 20 are stored in the secondary storage device 213 or the like in the form of a program, for example. Various functions are realized by executing information processing and arithmetic processing. In addition, the program may be provided in a form pre-installed in the secondary storage device 213, in a form stored in another non-temporary computer-readable storage medium, or via wired or wireless communication means. A form in which the data is distributed via the Internet may also be applied. Examples of non-temporary computer-readable storage media include magnetic disks, magneto-optical disks, CD-ROMs, DVD-ROMs, semiconductor memories, and the like.

The gantry control device 200 also includes an external interface 214, a communication interface 215, and the like. These units are connected to each other directly or indirectly via a bus, and cooperate with each other to perform various processes.

The external interface 214 is an interface for connecting with an external device. Examples of external devices include an external monitor, a USB memory, an external HDD, an external camera, and the like. Although only one external interface is shown in the example shown in FIG. 2, a plurality of external interfaces may be provided.

The communication interface 215 functions as an interface for connecting to a network, communicating with other devices, and transmitting and receiving information. The communication interface 215 communicates with other devices, for example, by wire or wirelessly. Examples of wireless communication include communication through lines such as Bluetooth (registered trademark), Wi-Fi, mobile communication systems (3G, 4G, 5G, 6G, LTE, etc.), satellite positioning systems, and wireless LANs. An example of wired communication is communication through a line such as a wired LAN (Local Area Network).

[Regarding the configuration of the communication base station]
The communication base station 30 relays communication between the aircraft 10 and the flight platform 20, communicates with the outside (aircraft 10, flight platform 20, and satellite positioning system), acquires and analyzes weather information, acquires and analyzes geographical information, It is a facility for grasping the positions of the aircraft 10 and the flight platform 20, determining the routes and trajectories of the aircraft 10 and the flight platform 20, and performing other processing necessary for the operation of the air takeoff and landing system 1.
This processing is executed by the base station controller 300 of the communication base station 30 .

As shown in FIG. 2, the base station controller 300 includes, for example, a CPU (Central Processing Unit: processor) 311, a main memory (main memory) 312, a secondary storage (secondary storage: memory) 313, and the like. there is

For example, the CPU 311 controls each device of the communication base station 30 by means of an OS (Operating System) stored in a secondary storage device 313 connected via a bus. Various processes are executed by executing various programs. One or a plurality of CPUs 311 may be provided and cooperate with each other to implement processing.

The main memory device 312 is composed of a writable memory such as a cache memory and a RAM (Random Access Memory), and is used as a work area for reading the execution program of the CPU 311 and writing processing data by the execution program. .

The secondary storage device 313 is a non-transitory computer readable storage medium. The secondary storage device 313 is, for example, a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, a semiconductor memory, or the like. Examples of the secondary storage device 313 include ROM (Read Only Memory), HDD (Hard Disk Drive), SSD (Solid State Drive) flash memory, and the like. The secondary storage device 313 includes, for example, an OS such as Windows (registered trademark), iOS (registered trademark), and Android (registered trademark) for controlling the entire information processing apparatus, BIOS (Basic Input/Output System), peripheral It stores various device drivers, various application software, and various data and files for hardware operation of devices. In addition, the secondary storage device 313 stores programs for implementing various processes and various data required for implementing various processes. A plurality of secondary storage devices 313 may be provided, and the above-described programs and data may be divided and stored in each secondary storage device 313 .

A series of processes for realizing the functions of the communication base station 30 are stored in the secondary storage device 313 or the like in the form of a program, for example. Various functions are realized by reading out and processing and arithmetic processing of information. In addition, the program may be provided in a form pre-installed in the secondary storage device 313, in a form stored in another non-temporary computer-readable storage medium, or via wired or wireless communication means. A form in which the data is distributed via the Internet may also be applied. Examples of non-temporary computer-readable storage media include magnetic disks, magneto-optical disks, CD-ROMs, DVD-ROMs, semiconductor memories, and the like.

The base station controller 300 also includes an external interface 314, a communication interface 315, and the like. These units are connected to each other directly or indirectly via a bus, and cooperate with each other to perform various processes.

The external interface 314 is an interface for connecting with an external device. Examples of external devices include an external monitor, a USB memory, an external HDD, an external camera, and the like. Although only one external interface is shown in the example shown in FIG. 2, a plurality of external interfaces may be provided.

The communication interface 315 functions as an interface for connecting to a network, communicating with other devices, and transmitting and receiving information. The communication interface 315 communicates with other devices, for example, by wire or wirelessly. Examples of wireless communication include communication through lines such as Bluetooth (registered trademark), Wi-Fi, mobile communication systems (3G, 4G, 5G, 6G, LTE, etc.), satellite positioning systems, and wireless LANs. An example of wired communication is communication through a line such as a wired LAN (Local Area Network).

[How to operate the flight platform (takeoff/launch)]
As shown in FIG. 6, the flight platform 20 with the aircraft 10 mounted thereon is raised (upward mode). This is not limited to vertical ascent, and may be ascent accompanied by movement. Thereby, the aircraft 10 takes off together with the flight platform 20 .
The flight platform 20 rises, for example, to an altitude of 1000m to 2000m.

Next, the flight platform 20 is dropped (dive, swoop down) in the air to convert the potential energy into velocity energy traveling in the direction of travel. In other words, like a glider, some of the velocity components generated by falling are used as velocity components in the direction of travel. This allows the flight platform 20 to be accelerated in the forward direction (acceleration mode). The flight platform 20 drops, for example, about 300m.
When dropping the flight platform 20, the flight platform 20 may be tilted forward in the direction of travel. As a result, the mounted aircraft 10 also leans forward, and lift generated by the main wings of the aircraft 10 can be maximized like a glider.

Here, "falling" means falling using the weight of the flight platform 20, which can be achieved, for example, by tilting the movable fan unit 24B to reduce the component of the thrust acting vertically downward.
“Forward leaning” means lowering the leading edge (the forward edge in the direction of travel) of the flight platform 20 than the trailing edge (the rearward edge in the direction of travel), thereby increasing the output of the fixed fan unit 24A. It can be realized by making the front and rear of the flight platform 20 different.

Also, by tilting the movable fan unit 24B, the acceleration of the flight platform 20 can be accelerated. That is, by using both the acceleration due to falling and the acceleration due to the electric fan 23, efficient acceleration can be realized.

When the speed of the flight platform 20 on which the aircraft 10 is mounted reaches the take-off speed of the aircraft 10 (for example, about 300 km/h), that is, when the aircraft 10 has enough lift to support its own weight, the aircraft 10 is released from the flight platform 20. take off. Also, the flight platform 20 ends the acceleration due to the fall.

The aircraft 10 and flight platform 20 then travel to their respective destinations.

[How to operate the flight platform (landing/landing)]
As shown in FIG. 7, the flight platform 20 without the aircraft 10 is raised. This is not limited to vertical ascent, and may be ascent accompanied by movement.
The flight platform 20 rises, for example, to an altitude of 1000m to 2000m.

Next, the flight platform 20 is dropped (dive, swoop down) in the air to convert the potential energy into velocity energy traveling in the direction of travel.
The principle is the same as during takeoff/launch.

The aircraft 10 approaches the accelerating flight platform 20 from behind.
Then, when the aircraft 10 catches up with the flight platform 20 and thereafter the speed of the flight platform 20 and the aircraft 10 becomes constant (for example, about 300 km/h), the acceleration due to the drop of the flight platform 20 ends.
The acceleration of the flight platform 20 may be terminated before the speed of the flight platform 20 and the aircraft 10 become constant, and the speed of the flight platform 20 and the aircraft 10 may be adjusted by adjusting the speed of the aircraft 10 .

After that, the aircraft 10 located above the mounting surface 22 lands on the flight platform 20 . At this time, the flight platform 20 supports the weight of the aircraft 10 in addition to its own weight.

The flight platform 20 carrying the aircraft 10 then lands at the destination. Landing may be vertical landing.

[Regarding the trajectory of the flight platform when it falls]
The trajectory of the flight platform 20 when it falls is not limited to a straight line as shown in FIGS. 6 and 7 .
For example, as shown in FIG. 8, the flight platform 20 may be rotated and dropped. At this time, the turning radius is, for example, about 2000m. Also, as shown in FIG. 9, the turning radius may be gradually reduced.
As a result, it is possible to prevent the flight platform 20 from being excessively separated from the point where the flight platform 20 started to drop.

For example, at the time of landing, by setting the turning center to the flight port P (destination), the aircraft 10 lands on the flight platform 20 above the flight port P, and then lands on the flight port P together with the flight platform 20. can do. At this time, since the flight platform 20 whose turning center is the flight port P is not excessively separated from the flight port P, the power consumed when the flight platform 20 moves to the flight port P can be reduced.

In order for the aircraft 10 to land safely on the flight platform 20 while turning in the air, the turning radius of the aircraft 10 must match the turning radius of the flight platform 20 .

The turning radius does not depend on the weight of the aircraft, but on the flight speed and bank.
Therefore, when the aircraft 10 chases the flight platform 20, the bank angle of the aircraft 10 becomes larger than the bank angle of the flight platform 20, as shown in FIG. In this state, the main wing of aircraft 10 contacts flight platform 20 . Therefore, when the aircraft 10 catches up with the flight platform 20, the aircraft 10 is decelerated. Then, the deceleration of the aircraft 10 and/or the acceleration of the flight platform 20 is terminated when the aircraft 10 reaches a constant speed (for example, about 300 km/h) on the flight platform 20 .

[About the basic operation method of the air takeoff and landing system]
The air takeoff and landing system 1 having the flight platform 20 as described above is operated, for example, as follows.

As shown in FIG. 11, a communication base station 30 is installed on the ground. The communication base station 30 may be installed at the flight port P, for example, or may be installed at another location away from the flight port P. Also, a controller may be assigned to the communication base station 30 .

The communication base station 30 transmits to the aircraft 10 the altitude and position at which the aircraft 10 can safely land on the flight platform 20 based on the obtained weather information and geographical information.
The aircraft 10 transmits to the communication base station 30 the expected time of arrival near the destination and other information about the aircraft 10 (expected landing speed, etc.).

The communication base station 30 sets the altitude to be climbed so that the flight platform 20 reaches a predetermined speed in the sky at the estimated arrival time of the aircraft 10 , and transmits a takeoff command to the flight platform 20 .
The flight platform 20 starts taking off based on a command from the communication base station 30 .

The communication base station 30 acquires information about flight conditions from the flight platform 20 and transmits information such as the altitude, turning radius and turning direction of the flight platform 20 to the aircraft 10 .

The aircraft 10 transmits the information to the communication base station 30 when entering the target turning orbit.
Communication base station 30 sends instructions to flight platform 20 to learn the position of aircraft 10 .
Means (image recognition section and distance measurement section) for the flight platform 20 to recognize the position of the aircraft 10 will be described later.

Once flight platform 20 recognizes the position of aircraft 10 , aircraft 10 begins landing on flight platform 20 . At this time, the attitude of the flight platform 20 is adjusted so as to maintain an appropriate position with the aircraft 10 .
Upon completion of landing on flight platform 20, aircraft 10 idles the engines.

In addition, as shown in FIG. 12, a radar 31 may be installed in the communication base station 30 to directly grasp the positions of the aircraft 10 and the flight platform 20 . This makes it possible to determine the altitude, turning radius, turning direction, etc. more accurately and appropriately.
However, until the aircraft 10 enters the range that can be identified by the radar 31, control is performed as usual based on the position information from the satellite positioning system transmitted from the aircraft 10. FIG.

[Wide area operation method of takeoff and landing system; Example 1]
As shown in FIG. 13, the aircraft 10 normally takes off from the base airport AP. The airport AP is used as the base of the aircraft 10 because it is possible to use maintenance facilities and refueling facilities provided in general airports.
On the other hand, the flight platform 20 takes off from the standby base B where the communication base station 30 is installed.
Aircraft 10 then lands on flight platform 20 in mid-air.

The flight platform 20 with the aircraft 10 on board makes a vertical landing at the first destination, flight port P1. Then, the aircraft 10 is loaded with passengers.
The flight port P1 is installed in a place where a space for constructing a runway cannot be secured, but the landing of the aircraft 10 is realized by vertically landing the flight platform 20 together with the aircraft 10. - 特許庁

Next, the flight platform 20 is vertically taken off together with the aircraft 10, moved to the second destination, the flight port P2, and landed vertically.
After that, this process is repeated.

Then, the aircraft 10 carrying passengers at the flight port P3, which is the third destination, takes off vertically together with the flight platform 20, takes off in the air from the flight platform 20, and reaches its final destination (for example, another airport). fly to
Meanwhile, the flight platform 20 returns to the standby base B where the communication base station 30 is installed.

Note that the number of flight ports is not particularly limited.
Also, when the flight platform 20 is vertically landed, the electric fan 23 may generate power. As a result, power consumption can be reduced as a whole.

[Wide area operation method of takeoff and landing system; Example 2]
As shown in FIG. 14, the flight platform 20 takes off from the standby base B where the communication base station 30 is installed in accordance with the arrival of the aircraft 10 .
Aircraft 10 then lands on flight platform 20 in mid-air.

The flight platform 20 with the aircraft 10 on board makes a vertical landing at the first destination, flight port P1. Passengers are then disembarked from the aircraft 10 .
The flight port P1 is installed in a place where a space for constructing a runway cannot be secured, but the landing of the aircraft 10 is realized by vertically landing the flight platform 20 together with the aircraft 10. - 特許庁

Next, the flight platform 20 is vertically taken off together with the aircraft 10, moved to the second destination, the flight port P2, and landed vertically.
After that, this process is repeated.

Then, the aircraft 10 that has unloaded passengers at the flight port P3, which is the third destination, takes off vertically together with the flight platform 20, takes off in the air from the flight platform 20, and flies to the base airport AP.
Meanwhile, the flight platform 20 returns to the standby base B where the communication base station 30 is installed.

[Additional configuration of the flight platform]
In addition to the basic configuration of the flight platform 20 described above, the following configuration may be added.

<Image recognition unit>
As shown in FIG. 15 , a camera (image recognition section) 41 may be provided in front of the flight platform 20 . The camera 41 is a device that captures the situation behind the flight platform 20 .
The camera 41 is installed at a predetermined angle α with respect to the mounting surface 22 . The angle α is, for example, about 3 degrees.
The camera 41 recognizes the aircraft 10 and navigation lights approaching from behind the flight platform 20 as images, and transmits the information to the platform control device 200 .

The cradle control device 200 grasps the relative positional relationship between the aircraft 10 and the flight cradle 20 based on the information.
As a result, as shown in FIG. 16, if the aircraft 10 is away from the reference position (the center of the cross), the gantry control device 200 adjusts the attitude and position of the flight platform 20 so that the aircraft 10 moves to the reference position. change.
As a result, safe landing of the aircraft 10 can be realized.

Further, the angle α of the camera 41 can be changed according to the model of the aircraft 10 and weather conditions. For example, when the aircraft 10 and the flight platform 20 sway greatly due to stormy weather, the angle α can be set to approximately 10 degrees to avoid collision between the aircraft 10 and the flight platform 20 .

Further, when the aircraft 10 and the flight platform 20 sway greatly due to stormy weather, as shown in FIG. good.

Also, in stormy weather or at night, the attitude and position of the aircraft 10 may be grasped by recognizing the navigation lights of the aircraft 10 with the camera 41 .

<Distance measuring device>
As shown in FIGS. 18 and 19 , a laser range finder (distance measuring device) 42 may be provided to measure the distance between the flight platform 20 and the aircraft 10 flying directly above the flight platform 20 .
The laser range finder 42 measures, for example, one point on the tip side of the fuselage of the aircraft 10 and one point on each main wing (three points in total).
The laser range finder 42 transmits information about the measured values to the gantry controller 200 .

The cradle control device 200 determines the oscillation cycle of the aircraft 10 based on the information, and raises the flight cradle 20 at the timing when the aircraft 10 becomes parallel to the flight cradle 20 .
As a result, safe landing of the aircraft 10 can be realized.

<Regarding the guide section and storage pit>
As shown in FIGS. 20 to 22, the flight platform 20 may be provided with a guide section 50 .
The guide portion 50 is a portion that protrudes upward from the mounting surface 22 of the flight platform 20 and is a portion that the wheels 11a of the main landing gear 11 first come into contact with when the aircraft 10 lands on the flight platform 20 .

The guiding part 50 has an inclined surface that becomes lower toward the rear of the flight platform 20 . The wheel 11a in contact with the guiding portion 50 moves along the inclined surface of the guiding portion 50 to a predetermined position.
This allows the aircraft 10 to be guided to the proper location on the flight platform 20 .

As shown in FIG. 23, a storage pit (concave shape) 61 is provided at a predetermined position to which the wheels 11a are guided.
The accommodation pit 61 forms a space capable of accommodating at least the lower half portion of the wheel 11a.
Thereby, the aircraft 10 can be stably mounted on the flight platform 20 .

Also, a stopper 51 may be provided at the front end of the guiding portion 50 . The stopper 51 is a portion that prevents the wheel 11 a from falling off from the front end of the guide portion 50 .
The height of the stopper 51 is such that it does not come into contact with the lower surface of the aircraft 10 mounted on the mounting surface 22 .

As shown in FIG. 24 , the guiding portion 50 may be accommodated in the gantry body 21 .
As a result, when the guide part 50 is not used (for example, when flying with the flight platform 20 alone), the guide part 50 can be prevented from becoming air resistance.
Further, air resistance may be reduced by providing a fairing 52 at the front end of the stopper 51, as shown in FIG.
Further, as shown in FIG. 26, the air resistance may be reduced by providing a through hole 53 penetrating from the front surface of the stopper 51 to the inclined surface of the guiding portion 50 .

As shown in FIG. 21 , in any case, the guide section 50 is preferably installed behind the center of gravity of the flight platform 20 in the traveling direction.
As a result, when the aircraft 10 lands on the flight platform 20, it is possible to prevent the flight platform 20 from rotating around the center of gravity due to the force FF that the guide section 50 receives from the wheels 11a.

Further, as shown in FIG. 27, the cross-sectional shape of the inclined surface of the guide portion 50 may be V-shaped or U-shaped.
As a result, the wheels 11 a can be brought to the center and stably guided to the storage pit 61 .
Further, by providing a plurality of rollers 54 on the inclined surface of the V-shaped or U-shaped guide portion 50, the wheel 11a can be smoothly moved to the center.

Further, as shown in FIGS. 28 and 29, a fixing pad (fixing portion) 62 may be provided to hold down the side surface of the wheel 11a accommodated in the accommodation pit 61. FIG.
Thereby, the aircraft 10 can be more stably mounted on the flight platform 20 .

<wing>
As shown in FIG. 30 , wings 70 may be provided on both side surfaces of the gantry body 21 .
As a result, the posture of the flight platform 20 can be stabilized when the flight platform 20 is dropped or when the flight platform 20 is rotated.
Also, part of the velocity component generated by the fall can be efficiently used as the velocity component in the traveling direction. In this case, when dropping the flight platform 20, it is preferable to tilt the flight platform 20 forward in the traveling direction like a glider.

As shown in FIGS. 31 and 32, the wing 70 is preferably composed of a framework 71 and a skin material 76 for weight reduction.
As shown in FIG. 31, the frame 71 includes a front spar 72 and a rear spar 73 protruding from the side surface of the gantry body 21, a front edge member 74 extending from the front corner of the gantry body 21 to the tip of the front spar 72, and the gantry body. 21 to the tip of the rear spar 73.
The wing 70 can be constructed by applying a bag-shaped skin material 76 as shown in FIG. The material of the skin material 76 is a flexible material (for example, a cloth material).

Wings 70 may be of the fixed type or may be of the deployable type as required.

The configuration of the expandable wings 70 is exemplified as follows.
That is, as shown in FIGS. 33 and 34, by sliding the front spar 72 and the rear spar 73, the framework 71 is configured to protrude from the side surface of the gantry body 21 or be accommodated in the gantry body 21. .
At this time, the front edge member 74 is rotatably connected to the front corner of the gantry body 21 at its base end, and rotatably and slidably connected to the tip of the front spar 72 at its distal end. The rear edge member 75 has a base end rotatably connected to the rear corner of the gantry main body 21 and a tip side portion rotatably and slidably connected to the tip of the rear spar 73 .
This allows the framework 71 to be deployed and retracted. That is, the wings 70 can be extended and folded.

The configuration of the tip portion of the front spar 72 will be described below.
As shown in FIGS. 35 and 36, a roller 72a is attached to the tip of the front spar 72. As shown in FIGS. Further, inside the front edge member 74, a groove 74a in which the roller 72a can slide is formed along the length direction of the front edge member 74. As shown in FIG.
A roller 72a provided at the tip of the front spar 72 rotates and slides in the groove 74a, so that the tip side portion of the front edge member 74 can rotate and slide to the tip of the front spar 72. will be connected to The same applies to the rear spar 73 and the rear edge member 75 .

A configuration for sliding the front spar 72 will be described below.
As shown in FIGS. 37 to 39 , the two front spars 72 overlap each other in the thickness direction of the gantry body 21 . Each front spar 72 slides toward the opposite side.

As shown in FIGS. 38 and 39 , a U-shaped recessed rack groove 72 b is formed along the length direction of the front spar 72 on each of the opposing surfaces of the two overlapping front spar 72 . ing. The bottom surface of each rack groove 72b is provided with a large number of teeth along the length direction of the rack groove 72b.

A gear 77 is interposed between the rack groove 72b formed in the upper front spar 72 and the rack groove 72b formed in the lower front spar 72. As shown in FIG.
The gear 77 meshes with teeth provided in the two rack grooves 72b. A rotating shaft 77 a of the gear 77 is fixed to the gantry body 21 .
Thereby, the movement of the upper front spar 72 and the movement of the lower front spar 72 can be synchronized. Also, the amount of movement of the upper front spar 72 and the amount of movement of the lower front spar 72 can be aligned. In other words, the two wings 70 provided on both side surfaces of the gantry body 21 can be extended at the same timing and with the same amount of projection. The same applies to the rear spar 73 as well.

The wings 70 may be deployed by driving the gear 77 or by using ram pressure.

A method for extending the wings 70 using ram pressure will be described below.
As shown in FIG. 40, by introducing air between the upper surface and the lower surface of the skin material 76, the wing 70 can be expanded by the momentum of the air.
This eliminates the need to separately provide a power source for extending the wing 70, that is, a separate power source for sliding the front spar 72 and the rear spar 73, and the weight of the flight platform 20 can be reduced.

Specifically, as shown in FIG. 41, a duct 78 is provided to communicate the lower surface and the side surface of the gantry body 21, and air is taken in from an intake port 78a by ram pressure and exhausted from an exhaust port 78b. The exhaust port 78 b opens inside the skin material 76 .
As a result, the air taken in from the intake port 78a can be introduced between the top surface and the bottom surface of the skin material 76 via the exhaust port 78b.

At this time, by connecting the upper surface and the lower surface of the skin material 76 with a plurality of wires 79 as shown in FIG. 42, the skin material 76 spread by the air can be kept in an ideal shape. Also, when folding the wings 70, it is possible to prevent the skin material 76 from unintentionally opening outward, so that the wings can be folded uniformly.
A high-strength thread may be used instead of the wire 79 .

According to this embodiment, the following effects are obtained.
That is, the flight platform 20 is raised, and while the raised flight platform 20 is dropped in the air, the velocity component generated by the fall is converted into the velocity component in the traveling direction. can be converted into velocity energy that travels to
As a result, compared to the case where the flight platform 20 is accelerated only by the electric fan 23, the flight platform 20 can be accelerated to a higher speed range. Therefore, even an aircraft 10 such as a jet aircraft can take off and land using the flight platform 20 .

In addition, when the flight platform 20 is dropped while rotating in the air, it is possible to prevent the flight platform 20 from being excessively separated from the point where the flight platform 20 started dropping due to the drop.

In addition, when the flight platform 20 is dropped while rotating around the flight port P, for example, at the time of landing, the aircraft 10 is landed on the flight platform 20 in the sky around the flight port P, and then the flight platform 20 You can land on flight port P. At this time, since the flight platform 20 whose turning center is the flight port P is not excessively separated from the flight port P, the power consumed when the flight platform 20 moves to the flight port P can be reduced.

In addition, the aircraft 10, such as a jet aircraft, can be safely started from the flight platform 20 by ending the acceleration due to the fall when the aircraft 10 mounted thereon has a lift force capable of supporting its own weight.

In addition, the aircraft 10 can be safely landed on the flight platform 20 by ending the acceleration due to the drop when the velocity becomes the same as that of the aircraft 10 positioned above the mounting surface 22 .

In addition to the flight platform 20 and the aircraft 10, the air takeoff and landing system 1 includes a communication base station 30 capable of communicating with the outside, and the communication base station 30 relays information between the flight platform 20 and the aircraft 10. and/or control of the system may be provided through the communication base station 30 when transmitting information and/or commands to the flight platform 20 and the aircraft 10 .
In addition, the communication base station 30 can issue various appropriate commands to the flight platform 20 and the aircraft 10 based on information (geographical information, weather information, etc.) obtained from the outside.

Further, when the communication base station 30 has a radar 31 for ascertaining the positions of the flight platform 20 and the aircraft 10, it is possible to directly ascertain the positions of the flight platform 20 and the aircraft 10, which is more accurate and , a suitable turning trajectory can be determined.

Further, when the flight platform 20 has a camera 41 that recognizes the position of the aircraft 10 , by adjusting the position relative to the aircraft 10 based on the information from the camera 41 , the aircraft 10 can move from the flight platform 20 When taking off from or landing on the flight platform 20, the positional relationship with the aircraft 10 can be made appropriate according to the situation.

Further, when the flight platform 20 has a laser range finder 42 capable of measuring the distance to the aircraft 10 positioned above the mounting surface 22 at a plurality of points, the distance of the aircraft 10 can be measured based on the information of the laser range finder 42 . By determining the swing period, the flight platform 20 can be raised at the timing when the aircraft 10 becomes parallel to the flight platform 20 .

In addition, the flight platform 20 is installed on the mounting surface 22 and includes a guide portion 50 that contacts the wheels 11a of the main landing gear 11 of the aircraft 10 and guides the contacted wheels 11a to a predetermined position on the mounting surface 22. In that case, when the aircraft 10 lands on the flight platform 20 , the aircraft 10 can be guided to an appropriate location on the flight platform 20 .

Further, when the guide part 50 can be accommodated in the gantry main body 21 below the mounting surface 22, when the guide part 50 is not used (for example, when flying with the flight cradle 20 alone), the guide part 50 Avoid air resistance.

In addition, when the guide unit 50 is installed behind the center of gravity of the entire flight platform 20 in the traveling direction, the force ( Forward force) can prevent the flight platform 20 from rotating about the center of gravity.

Further, when the flight platform 20 is installed in the platform body 21 and has a storage pit 61 in which the guided wheels 11a are accommodated, the aircraft 10 can be stably mounted on the flight platform 20.

In addition, when the flight platform 20 is provided with fixing pads 62 for fixing the wheels 11a housed in the storage pits 61, the aircraft 10 can be mounted on the flight platform 20 more stably.

In addition, when the flight platform 20 has wings 70 installed on both sides of the platform body 21, the attitude of the flight platform 20 can be stabilized during a fall or during a swing during a fall.

Further, when the wing 70 has the framework 71 and a flexible skin material 76 stretched on the framework 71, the weight of the wing 70 can be reduced.

Further, when the wings 70 can be accommodated in the gantry body 21 and can be extended from the cradle body 21, for example, the posture of the flight platform 20 can be stabilized by extending the wings 70 when falling. Also, for example, by accommodating the wings 70 when the flight platform 20 takes off and lands, it is possible to reduce the space occupied by the flight platform 20 at the takeoff and landing site.

Further, when the wing 70 is deployed using ram pressure generated by flight, there is no need to provide a separate power source for deploying the wing 70 . Therefore, the weight of the flight platform 20 can be reduced.

One embodiment explained as above is grasped as follows, for example.
That is, a method of operating a flight cradle (20) according to an aspect of the present disclosure includes a cradle body (21) provided with a mounting surface (22) on which an aircraft (10) can be mounted, and A method of operating a flight platform having a plurality of electric fans (23), wherein the flight platform is lifted, and while the lifted flight platform is dropped in the air, the velocity component generated by the drop is distributed in the traveling direction. Convert to velocity component.

According to the method of operating the flight platform according to this aspect, the flight platform is raised, and while the raised flight platform is dropped in the air, the velocity component generated by the drop is converted into the velocity component in the traveling direction. Potential energy obtained by ascent can be converted into velocity energy traveling in the direction of travel. As a result, the flight platform can be accelerated to a higher speed range than when the flight platform is accelerated only by the electric fan. Therefore, even an aircraft such as a jet plane can take off and land using the flight platform.

In addition, in a method for operating a flight platform according to an aspect of the present disclosure, the flight platform is dropped while rotating in the air.

According to the method of operating the flight platform according to this aspect, the flight platform is dropped while rotating in the air, so it is possible to avoid the flight platform from being excessively separated from the point where the flight platform started dropping due to the drop.
For example, at the time of landing, by setting the turning center as the flight port (destination), the aircraft can be landed on the flight platform above the flight port, and then landed on the flight port together with the flight platform. At this time, since the flight platform with the flight port as the center of rotation is not excessively separated from the flight port, the power consumed when the flight platform moves to the flight port can be reduced.

Further, in the flight platform operation method according to one aspect of the present disclosure, the acceleration due to the fall is terminated when the aircraft mounted on the mounting surface has a lift force capable of supporting its own weight.

According to the method of operating the flight platform according to this aspect, when the aircraft mounted on the mounting surface has enough lift to support its own weight, the acceleration due to the fall is terminated, so the aircraft can be safely launched from the flight platform. can.

Further, in the flight platform operation method according to one aspect of the present disclosure, the acceleration due to the fall is terminated when the speed becomes the same as that of the aircraft positioned above the mounting surface.

According to the method of operating the flight platform according to this aspect, the acceleration due to the drop is terminated when the speed becomes equal to that of the aircraft positioned above the mounting surface, so the aircraft can be safely landed on the flight platform.

A method of operating an aerial takeoff and landing system (1) according to an aspect of the present disclosure includes a gantry body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans housed in the gantry body. A method of operating a platform, the aircraft having a propulsion device, and an air takeoff and landing system equipped with the aircraft, wherein the flight platform is raised while the aircraft is mounted on the mounting surface, and the aircraft is mounted on the mounting surface. While the flight platform is dropped in the air while being mounted, the velocity component generated by the drop is converted into a velocity component in the direction of travel, and when the aircraft has a lift force capable of supporting its own weight, the aircraft is launched into the flight. Launch from the pedestal.

According to the operation method of the aerial takeoff and landing system according to this aspect, the flight platform and the aircraft having the propulsion device are provided, and the flight platform is lifted while the aircraft is mounted on the mounting surface, and the aircraft is mounted. While the flight platform is dropped in the air, the velocity component generated by the drop is converted into the velocity component in the direction of travel, so compared to the case where the flight platform is accelerated only by the electric fan, the flight platform can be moved to a higher speed range. can be accelerated.
In addition, since the aircraft is launched from the flight platform when it has enough lift to support its own weight, even an aircraft such as a jet aircraft can be launched using the flight platform.

Further, a method of operating an air takeoff and landing system according to an aspect of the present disclosure includes a gantry body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans, wherein the plurality of electric fans are attached to the gantry body. A method of operating an air landing system comprising a stowed flight platform and the aircraft having a propulsion device, the method comprising: raising the flight platform without the aircraft mounted on the mounting surface; While the aircraft is not mounted on the mounting surface, the flight platform is dropped in the air, and a velocity component generated by the fall is converted into a velocity component in the traveling direction, and accelerated onto the mounting surface of the flight platform. Land the aircraft.

According to the operation method of the aerial takeoff and landing system according to this aspect, the flight platform and the aircraft having the propulsion device are provided, and the flight platform is raised in a state in which the aircraft is not mounted on the mounting surface, and the aircraft is mounted. While the flight platform is dropped in the air without a fan, the velocity component generated by the drop is converted into a velocity component in the direction of travel. It can be accelerated up to the
Further, since the aircraft is landed on the mounting surface of the accelerated flight platform, even an aircraft such as a jet can be landed using the flight platform.

Further, a method of operating an air takeoff and landing system according to an aspect of the present disclosure includes a communication base station (30) capable of communicating with the flight platform, the aircraft, and the outside, and the communication base station comprises the flight platform and the aircraft. and/or transmit information and/or commands to the flight platform and the aircraft.

According to the operation method of the air takeoff and landing system according to this aspect, the flight platform, the aircraft, and a communication base station capable of communicating with the outside are provided, the communication base station relays information between the flight platform and the aircraft, and/ Alternatively, the system can be managed through a communication base station to transmit information and/or commands to the flight platform and aircraft. Also, based on externally obtained information (geographical information, weather information, etc.), the communication base station can issue various appropriate commands to the flight platform and the aircraft.

Further, in the operation method of the air takeoff and landing system according to one aspect of the present disclosure, the flight platform is dropped while being rotated.

According to the operation method of the aerial takeoff and landing system according to this aspect, the flight platform is dropped while rotating, so that the flight platform can be prevented from being excessively separated from the point where the flight platform started to drop due to the drop.

Further, in the operation method of the air takeoff and landing system according to one aspect of the present disclosure, the flight platform is dropped while rotating about the flight port (P).

According to the operation method of the aerial takeoff and landing system according to this aspect, the flight platform is dropped while rotating about the flight port. The aircraft can be landed on the flight platform in the air above the , and then landed on the flight port together with the flight platform. At this time, since the flight platform with the flight port as the center of rotation is not excessively separated from the flight port, the power consumed when the flight platform moves to the flight port can be reduced.

Further, in the method of operating an air takeoff and landing system according to an aspect of the present disclosure, the communication base station has a radar (31) for grasping the positions of the flight platform and the aircraft, and the position of the flight platform and the aircraft is detected. Determine the turning trajectory based on

According to the air take-off and landing system operation method according to this aspect, the communication base station has a radar for grasping the positions of the flight platform and the aircraft, and determines the turning trajectory based on the positions of the flight platform and the aircraft. By knowing the positions of the flight platform and the aircraft in real time, it is possible to determine a more accurate and appropriate turning trajectory.

Further, in the method of operating an air takeoff and landing system according to an aspect of the present disclosure, the flight platform has an image recognition unit (41) that recognizes the position of the aircraft, and based on the information of the image recognition unit, the aircraft Adjust the position relative to

According to the operation method of the aerial takeoff and landing system according to this aspect, the flight platform has an image recognition unit that recognizes the position of the aircraft, and adjusts the position relative to the aircraft based on information from the image recognition unit. , when the aircraft takes off from the flight platform or disembarks on the flight platform, the positional relationship with the aircraft can be made appropriate according to the situation.

Further, in the method of operating an air takeoff and landing system according to an aspect of the present disclosure, the flight platform has a distance measuring unit (42) capable of measuring a distance from the aircraft positioned above the mounting surface at a plurality of points. Then, the oscillation period of the aircraft is determined based on the information from the distance measuring unit.

According to the operation method of the aerial takeoff and landing system according to this aspect, the flight platform has a distance measuring unit capable of measuring the distance from the aircraft positioned above the mounting surface at a plurality of points, and based on the information of the distance measuring unit Since the swing period of the aircraft is determined by the operation, the flight platform can be raised at the timing when the aircraft becomes parallel to the flight platform.

A flight platform according to an aspect of the present disclosure includes a platform body provided with a mounting surface on which an aircraft can be mounted, a plurality of electric fans housed in the platform body, and a platform control device (200), The gantry control device performs an ascent mode for raising the flight cradle, and an acceleration mode for dropping the raised flight cradle in the air and converting a velocity component generated by the drop into a velocity component in the traveling direction.

According to the flight platform according to this aspect, it includes a platform body provided with a mounting surface on which an aircraft can be mounted, a plurality of electric fans housed in the platform body, and a platform control device. A climb mode that raises the platform and an acceleration mode that converts the velocity component generated by falling while dropping the raised flight platform in the air into the velocity component in the traveling direction. Energy can be converted into velocity energy traveling in the direction of travel. As a result, the flight platform can be accelerated to a higher speed range than when the flight platform is accelerated only by the electric fan. Therefore, even an aircraft such as a jet plane can take off and land using the flight platform.

The flight platform according to one aspect of the present disclosure is installed on the mounting surface, contacts the wheels (11a) of the main landing gear (11) of the aircraft, and guides the wheels in contact to a predetermined position on the mounting surface. It is provided with a guide (50) for

According to the flight platform according to this aspect, the guide section is installed on the mounting surface, contacts the wheels of the main landing gear of the aircraft, and guides the wheels in contact with the wheels to a predetermined position on the mounting surface. When landing on the flight platform, the aircraft can be guided to the appropriate location on the flight platform.

In the flight platform according to one aspect of the present disclosure, the guide section can be accommodated in the platform body below the mounting surface.

According to the flight platform according to this aspect, the guidance part can be accommodated in the platform body below the mounting surface. It is possible to avoid that the part becomes air resistance.

In the flight platform according to one aspect of the present disclosure, the guide section is installed behind the center of gravity of the entire aircraft in the traveling direction.

According to the flight platform according to this aspect, since the guide section is installed behind the position of the center of gravity of the entire aircraft in the traveling direction, the force ( Forward force) can prevent the flight platform from rotating around the center of gravity.

A flight cradle according to one aspect of the present disclosure comprises a recess (61) located in the cradle body for receiving the guided wheel.

According to the flight platform according to this aspect, the aircraft can be stably mounted on the flight platform because the recess is provided in the platform body and accommodates the guided wheels.

A flight platform according to one aspect of the present disclosure includes a securing portion (62) that secures the wheel housed in the recess.

According to the flight platform according to this aspect, since the fixing portion for fixing the wheels housed in the recess is provided, the aircraft can be mounted on the flight platform in a more stable manner.

A flight platform according to one aspect of the present disclosure includes wings (70) located on both sides of the platform body.

According to the flight platform according to this aspect, since the wings are provided on both sides of the platform body, the attitude of the flight platform can be stabilized when it falls or when it swings during a fall.

In a flight platform according to one aspect of the present disclosure, the wing has a framework (71) and a flexible skin material (76) stretched over the framework.

According to the flight platform according to this aspect, the wing has the framework and the flexible skin material stretched on the framework, so that the weight of the wing can be reduced.

In the flight cradle according to one aspect of the present disclosure, the wing is retractable into and extendable from the cradle body.

According to the flight platform according to this aspect, the wings can be accommodated in the platform body and can be extended from the platform body. can be made
Also, for example, by retracting the wings when the flight platform takes off and lands, the space occupied by the flight platform at the takeoff and landing site can be reduced.

In the flight platform according to one aspect of the present disclosure, the wings are deployed using ram pressure generated by flight.

According to the flight platform according to this aspect, the wings are deployed using the ram pressure generated by flight, so there is no need to provide a separate power source for deploying the wings. Therefore, the weight of the flight platform can be reduced.

10 Aircraft 11 Main Landing Gear 11a Wheel 20 Flight Platform 21 Platform Body 22 Mounting Surface 23 Electric Fan 24 Fan Unit 24A Fixed Fan Unit 24B Movable Fan Unit 30 Communication Base Station 31 Radar 41 Camera (Image Recognition Unit)
42 laser rangefinder (distance measuring unit)
50 guide part 51 stopper 52 fairing 53 through hole 54 roller 61 accommodation pit 62 fixing pad 70 wing 71 frame 72 front spar 72a roller 72b rack groove 73 rear spar 74 front edge material 74a groove 75 rear edge material 76 skin material 77 gear 77a Rotating shaft 78 Duct 78a Air inlet 78b Air outlet 79 Wire 100 Aircraft control device 200 Mount control device 300 Base station control device

Claims (22)

A method of operating a flight cradle having a cradle body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans housed in the cradle body, comprising:
raising the flight platform;
A method of operating a flight platform, wherein the flight platform that has risen is dropped in the air and a velocity component generated by the drop is converted into a velocity component in the traveling direction. 2. The method of operating a flight platform according to claim 1, wherein the flight platform is dropped while rotating in the air. 3. The method of operating a flight platform according to claim 1 or 2, wherein the acceleration due to falling is terminated when the aircraft mounted on the mounting surface has a lift force capable of supporting its own weight. 3. The method of operating a flight platform according to claim 1 or 2, wherein the acceleration due to the drop is terminated when the speed becomes equal to that of the aircraft positioned above the mounting surface. a flight cradle having a cradle body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans housed in the cradle body;
the aircraft having a propulsion device;
A method of operating an air takeoff and landing system comprising
raising the flight platform while the aircraft is mounted on the mounting surface;
While the aircraft is mounted on the mounting surface, the flight platform is dropped in the air, and a velocity component generated by the drop is converted into a velocity component in the traveling direction,
A method of operating an air takeoff and landing system for launching the aircraft from the flight platform when the aircraft has enough lift to support its own weight. A flight cradle having a cradle body provided with a mounting surface on which an aircraft can be mounted, and a plurality of electric fans, wherein the plurality of electric fans are accommodated in the cradle body;
the aircraft having a propulsion device;
A method of operating an air takeoff and landing system comprising
raising the flight platform while the aircraft is not mounted on the mounting surface;
While the aircraft is not mounted on the mounting surface, the flight platform is dropped in the air, and a velocity component generated by the drop is converted into a velocity component in the traveling direction,
A method of operating an air takeoff and landing system for landing the aircraft on the mounting surface of the flight platform that has been accelerated. A communication base station capable of communicating with the flight platform, the aircraft and the outside,
7. Aerial take-off and landing according to claim 5 or 6, wherein the communication base station relays information between the flight platform and the aircraft and/or transmits information and/or commands to the flight platform and the aircraft. How the system operates. 8. The method of operating an aerial takeoff and landing system according to claim 7, wherein the flight platform is dropped while being rotated. 9. The method of operating an aerial takeoff and landing system according to claim 8, wherein the flight platform is dropped while rotating around the flight port. 10. The air take-off and landing system according to claim 8 or 9, wherein the communication base station has a radar for ascertaining the positions of the flight platform and the aircraft, and determines a turning trajectory based on the positions of the flight platform and the aircraft. Operation method. The flight platform has an image recognition unit that recognizes the position of the aircraft,
11. The method of operating an aerial takeoff and landing system according to any one of claims 5 to 10, wherein the position relative to the aircraft is adjusted based on information from the image recognition unit. The flight platform has a distance measuring unit capable of measuring a distance from the aircraft positioned above the mounting surface at a plurality of points,
12. The method of operating an air takeoff and landing system according to any one of claims 5 to 11, wherein the oscillation period of the aircraft is determined based on the information from the distance measuring unit. A frame main body provided with a mounting surface on which an aircraft can be mounted;
a plurality of electric fans housed in the gantry body;
a gantry controller;
with
The gantry control device performs a lift mode for raising the flight cradle, and an acceleration mode for dropping the raised flight cradle in the air and converting a velocity component generated by the fall into a velocity component in the traveling direction. . 14. The flight platform according to claim 13, further comprising a guiding part installed on the mounting surface, contacting a wheel of the main landing gear of the aircraft, and guiding the contacting wheel to a predetermined position on the mounting surface. 15. The flight platform according to claim 14, wherein the guide portion can be accommodated in the platform body below the mounting surface. 16. The flight platform according to claim 14 or 15, wherein the guiding part is installed behind the position of the center of gravity of the whole in the traveling direction. 17. A flight platform according to any one of claims 14 to 16, comprising a recess in which the guided wheels are accommodated and located in the platform body. 18. A flight platform according to claim 17, comprising fixings for fixing the wheels received in the recesses. 19. The flight platform according to any one of claims 13 to 18, comprising wings installed on both sides of the platform body. 20. The flight platform of Claim 19, wherein the wing comprises a framework and a flexible skin material stretched over the framework. 21. The flight cradle of claim 20, wherein the wings are retractable into and extendable from the cradle body. 22. The flight platform of Claim 21, wherein the wings deploy using ram pressure generated by flight.