JP2022063525A - Flight cradle and takeoff/landing support system, and flight cradle operation method and takeoff/landing support system operation method - Google Patents

Abstract

To provide a flight cradle that does not require an airstrip and can safely perform takeoff/landing of an aircraft, and a takeoff/landing support system, and a flight cradle operation method and a takeoff/landing support system operation method.SOLUTION: A flight cradle 20 comprises: a cradle body 21 on a top face of which a loading surface 22 capable of loading an aircraft 10 is provided; and a plurality of electric fans 23. The plurality of electric fans 23 are accommodated in the cradle body 21. Further, a takeoff/landing support system comprises: the flight cradle 20; and the aircraft 10 having a propulsion unit. The flight cradle 20 elevates in a state that the aircraft 10 is loaded on the loading surface 22, and the flight cradle 20 accelerates and advances in the state that the aircraft 10, in which the propulsion unit has started, is loaded thereon, and leaves the aircraft 10 at a time point when the aircraft 10 comes to have a lift force that can support a self-weight thereof.SELECTED DRAWING: Figure 4

Description

The present disclosure relates to a flight gantry, a takeoff and landing support system, an operation method of the flight gantry, and an operation method of the takeoff and landing support system.

Fixed-wing aircraft are suitable for long-distance transport, but the available locations are limited due to the need for a runway during takeoff and landing. In particular, in places such as urban centers, mountainous areas, and remote islands, it is often not possible to secure space for constructing runways, and in such places, the transportation of people and goods by fixed-wing aircraft may be restricted. be.

Here, for example, Patent Document 1 discloses a technique for taking off and landing an aircraft on a flightable platform, and the aircraft can be taken off and landed without a runway.

U.S. Patent No. 5000388

However, in the configuration described in Patent Document 1, a device (fan or the like) for generating thrust is installed on the platform on which the aircraft takes off and landing, which may hinder the aircraft from taking off and landing.

The present disclosure has been made in view of such circumstances, and the flight pedestal and the takeoff and landing support system that do not require a runway and can safely take off and land the aircraft, the operation method of the flight pedestal, and the operation of the takeoff and landing support system. The purpose is to provide a method.

In order to solve the above problems, the following means shall be adopted for the flight gantry and takeoff and landing support system of the present disclosure, the operation method of the flight gantry, and the operation method of the takeoff and landing support system.
That is, the flight pedestal according to one aspect of the present disclosure includes a gantry main body having a mounting surface on the upper surface on which an aircraft can be mounted, and a plurality of electric fans, and the plurality of electric fans are housed in the gantry main body. Has been done.

Further, the takeoff and landing support system according to one aspect of the present disclosure includes the above-mentioned flight pedestal and the aircraft having a propulsion device, and the flight gantry rises with the aircraft mounted on the mounting surface. The flight pedestal accelerates and advances with the aircraft on which the propulsion device has been started, and separates from the aircraft when the aircraft has lift that can support its own weight.

Further, the operation method of the flight pedestal according to one aspect of the present disclosure includes a step of ascending with the aircraft mounted on the mounting surface and lift until the aircraft mounted on the mounting surface can support its own weight. It includes a step of accelerating and advancing, and a step of descending with the aircraft mounted on the mounting surface.

Further, the operation method of the takeoff and landing support system according to one aspect of the present disclosure includes a step in which the flight pedestal rises with the aircraft mounted on the mounting surface, and the flight pedestal in which the propulsion device is started. A takeoff and landing support system that includes a step of accelerating and advancing with an aircraft on board and leaving the aircraft when the aircraft has lift to support its own weight.

According to the present disclosure, no runway is required and the aircraft can be safely taken off and landed.

It is a perspective view of the flight pedestal (when mounted on an aircraft) which concerns on 1st Embodiment. It is a top view of the flight pedestal (when the aircraft is not mounted) which concerns on 1st Embodiment. It is a side view of the flight pedestal shown in FIG. It is a top view of the flight pedestal (when mounted on an aircraft) which concerns on 1st Embodiment. It is a top view of the flight pedestal shown in FIG. 4 in the state where the mounting surface is expanded. It is a top view of the flight pedestal (when the aircraft is not mounted) which concerns on 1st Embodiment. It is a side view of the flight pedestal when the fan unit is tilted in the flight pedestal which concerns on 1st Embodiment. It is a figure which shows from the takeoff to the landing of an aircraft in the takeoff / landing support system which concerns on 1st Embodiment. It is a side view which shows the state that the flight pedestal carrying an aircraft is taking off vertically in the takeoff and landing support system which concerns on 1st Embodiment. It is a side view which shows the state that the flight pedestal is accelerating and advancing in the takeoff and landing support system which concerns on 1st Embodiment. It is a side view which shows the appearance that the flight pedestal has separated from an aircraft in the takeoff and landing support system which concerns on 1st Embodiment. It is a side view which shows the state that the aircraft is approaching from the rear of the flight pedestal in the takeoff and landing support system which concerns on 1st Embodiment. It is a perspective view which shows the state that the aircraft is approaching from the rear of the flight pedestal in the takeoff and landing support system which concerns on 1st Embodiment. It is a side view which shows the state that the aircraft is landing on the flight pedestal in the takeoff and landing support system which concerns on 1st Embodiment. It is a side view which shows the state that the aircraft landed on the flight pedestal in the takeoff and landing support system which concerns on 1st Embodiment. It is a side view which shows the state that the flight pedestal carrying an aircraft is landing vertically in the takeoff and landing support system which concerns on 1st Embodiment. It is a perspective view of the flight pedestal (when the aircraft is not mounted) which concerns on 2nd Embodiment. It is a top view of the flight pedestal (when the aircraft is not mounted) which concerns on 2nd Embodiment. It is a side view which shows the state which the arresting wire surfaced in the flight pedestal which concerns on 2nd Embodiment. It is a side view which shows the state that the aircraft is approaching from the rear of the flight pedestal in the takeoff and landing support system which concerns on 2nd Embodiment. It is a side view which shows the state which the arresting hook of an aircraft was hooked on the arresting wire of a flight pedestal in the takeoff and landing support system which concerns on 2nd Embodiment. It is a side view which shows the appearance that the aircraft is drawn to the flight pedestal in the takeoff and landing support system which concerns on 2nd Embodiment. It is a top view of the flight pedestal shown in FIG. 22. It is a side view which shows the state that the main landing gear of an aircraft is mounted on the flight pedestal in the takeoff and landing support system which concerns on 2nd Embodiment. It is a top view of the flight pedestal shown in FIG. 24. It is a side view which shows the appearance that the aircraft is mounted on the flight pedestal in the takeoff and landing support system which concerns on 2nd Embodiment. It is a top view of the flight pedestal shown in FIG. 26. It is a side view of the flight pedestal which concerns on a modification.

[First Embodiment]
Hereinafter, the flight pedestal and the takeoff and landing support system, the operation method of the flight gantry, and the operation method of the takeoff and landing support system according to the first embodiment of the present disclosure will be described with reference to the drawings.

As shown in FIG. 1, the flight pedestal 20 is a device capable of flying with the aircraft 10 mounted on the upper surface (mounting surface 22), and constitutes a takeoff and landing support system together with the aircraft 10.

As shown in FIG. 2, the flight gantry 20 includes a gantry main body 21 and a plurality of electric fans 23.

The gantry main body 21 has skeletons assembled in a grid pattern, and each skeleton is rigidly connected and integrated.

As shown in FIGS. 2 and 3, a plurality of electric fans 23 are housed in the gantry main body 21. The electric fan 23 is driven by an electric motor to generate thrust.

As shown in FIG. 2, the electric fans 23 are arranged in a grid pattern. In the case of the figure, they are arranged in a grid pattern of 16 rows × 14 columns. By arranging the electric fans 23 in a grid pattern, the electric fans 23 can be efficiently provided in a dense state.
The number of electric fans 23 can be appropriately changed according to the specifications of the flight platform 20 and the weight of the aircraft 10 to be mounted.

As shown in FIG. 3, the electric fan 23 housed in the gantry main body 21 does not protrude from the upper surface of the gantry main body 21. As a result, the upper surface of the flight platform 20 becomes flat.

As shown in FIG. 4, a mounting surface 22 on which the aircraft 10 is mounted is provided on the upper surface of the gantry main body 21 in a flat state. The mounting surface 22 is preferably symmetrical with respect to the center of gravity of the gantry main body 21.
Batteries, control devices, communication devices, and the like necessary for operating the flight gantry 20 may be housed in the lower portion of the mounting surface 22 (inside the flight gantry 20).

As shown in FIG. 5, the range of the mounting surface 22 may be changed (for example, expanded) by providing a plate-shaped cover member 25 on the upper portion of the gantry main body 21 (electric fan 23). Thereby, the shape of the mounting surface 22 can be arbitrarily changed according to the position of the legs of the aircraft 10. Further, the electric fan 23 at the position where the cover member 25 is provided may be removed from the gantry main body 21, and the number of electric fans 23 can be changed according to the weight of the machine body. Even when the range of the mounting surface 22 is changed, it is preferable that the mounting surface 22 is symmetrical with respect to the center of gravity of the gantry main body 21.
Further, the cover member 25 may be used as a member that temporarily protects the electric fan 23 when the aircraft 10 is moved on the flight platform 20. In this case, the cover member 25 will be removed after the aircraft 10 is mounted.

As shown in FIG. 6, the plurality of electric fans 23 constitute a fan unit 24 having a total of four units of 2 rows × 2 columns as one set. The fan unit 24 includes two types, a fixed fan unit 24A and a movable fan unit 24B.
The cross-hatching shown in FIG. 6 is drawn so that the fixed fan unit 24A and the movable fan unit 24B can be easily distinguished from each other in appearance in explaining the present embodiment, and is an element constituting the flight pedestal 20. is not.

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

As shown in FIG. 7, each movable fan unit 24B can be tilted in the front-rear direction with respect to the gantry main body 21. As a result, the airflow can be sent in the rear-downward direction or the front-downward direction without tilting the flight platform 20 itself. That is, it is possible to generate a thrust that advances forward or backward while maintaining an upward thrust.
It is not always necessary to tilt all the movable fan units 24B in the same direction by the same angle, and the tilt direction and angle may be different for each movable fan unit 24B. Further, it is not always necessary to tilt each movable fan unit 24B, and a configuration that tilts each electric fan 23 may be adopted.

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

Further, in the four electric fans 23 constituting one fixed fan unit 24A, two electric fans 23 adjacent to each other in the diagonal direction rotate in the same direction at the same rotation speed, and the row direction (column direction). Two adjacent electric fans 23 are configured to rotate in different directions, and by adjusting the rotation speed of the adjacent electric fans 23 in the row direction (column direction), the yaw direction of the flight gantry 20 is adjusted. The posture can be controlled.

The rotation speed of each electric fan 23 and the tilt angle of the fan unit 24 are controlled by a control unit (not shown).

The control unit can communicate with each electric fan 23, sensors attached to various places, external equipment (for example, GCS (Ground Control System) and GPS), aircraft 10, and other devices constituting this system. , The rotation speed of the electric fan 23, the posture and position of the flight platform 20, and the like are grasped and controlled.

The control unit is composed of, for example, a CPU (Central Processing Unit), a RAM (Random Access Memory), a ROM (Read Only Memory), a computer-readable storage medium, and the like.
As an example, a series of processes for realizing various functions are stored in a storage medium or the like in the form of a program, and the CPU reads this program into a RAM or the like to execute information processing / arithmetic processing. As a result, various functions are realized.
The program is installed in a ROM or other storage medium in advance, is provided in a state of being stored in a computer-readable storage medium, or is distributed via a wired or wireless communication means. Etc. may be applied.
The computer-readable storage medium is a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, a semiconductor memory, or the like.

The takeoff and landing support system configured as described above is operated as follows.
That is, as shown in FIGS. 8 and 9, at the time of takeoff, the electric fan 23 is driven with the aircraft 10 mounted on the mounting surface 22 of the flight platform 20 to take off vertically (takeoff mode). At this time, the legs of the aircraft 10 are fixed to the mounting surface 22.

After ascending vertically, the propulsion device of the aircraft 10 (for example, an electric fan or a jet engine) is started. As shown in FIG. 10, when the propulsion device is started (or at the same time as the start), the movable fan unit 24B is tilted forward to accelerate while increasing the altitude (acceleration mode).

The propulsion device of the aircraft 10 may be started on the ground and the flight platform 20 may be raised in an idle state.

As the acceleration continues, lift is generated on the fixed wing of the aircraft 10. As shown in FIGS. 8 and 11, when the aircraft 10 has a lift sufficient to support its own weight, the aircraft 10 and the flight gantry 20 are released from the fixation and the thrust of the electric fan 23 is reduced. As a result, the flight platform 20 is separated from the aircraft 10, and the aircraft 10 flies as it is.
Whether or not sufficient lift is generated in the aircraft 10 can be determined by measuring the load received by the flight platform 20 from the aircraft 10 with a sensor and monitoring it with the control unit.

The detached flight gantry 20 can return to the takeoff point. Therefore, since the flight pedestal 20 detached from the system does not fly for a long time, the mounted battery can be miniaturized.

As shown in FIGS. 8 and 12, at the time of landing, another flight gantry 20 waiting at the landing point and the aircraft 10 approach each other in parallel. At this time, as shown in FIG. 13, the aircraft 10 is guided to the flight gantry 20 by transmitting a guided radio wave from the flying flight gantry 20 to the aircraft 10. Further, a light source may be provided on the flight platform 20 to improve visibility from the aircraft 10.

As shown in FIG. 14, when the relative speed between the aircraft 10 and the flight gantry 20 becomes zero, the aircraft 10 is mounted and fixed on the flight gantry 20 again as shown in FIG. After the aircraft 10 is mounted on the flight platform 20, the propulsion device of the aircraft 10 is stopped.

After that, as shown in FIGS. 8 and 16, the flight platform 20 on which the aircraft 10 is mounted makes a vertical landing by controlling the thrust and tilt angle of the electric fan 23 (landing mode).

It is not necessary to stop the propulsion device of the aircraft 10 immediately after the aircraft 10 is mounted on the flight gantry 20, and the propulsion device of the aircraft 10 may be stopped during the descent of the flight gantry 20 or after landing.

According to this embodiment, the following effects are obtained.
A gantry main body 21 having a mounting surface 22 on which an aircraft 10 can be mounted is provided on the upper surface, and a plurality of electric fans 23. Since the plurality of electric fans 23 are housed in the gantry main body 21, the electric fan 23 By thrust, it is possible to take off vertically together with the flight platform 20 with the aircraft 10 mounted.

Further, the aircraft 10 accelerates and advances together with the flight platform 20 until the aircraft 10 has lift, and when the lift of the aircraft 10 exceeds the weight of the aircraft 10, the aircraft 10 flies by its own propulsion device (for example, a jet engine or an electric fan). You can fly away from the gantry 20. This allows the aircraft 10 to take off and be ready to fly without a runway.

Further, since the aircraft 10 rises (vertical takeoff) by the thrust of the flight platform 20 instead of its own thrust, it does not consume as much fuel as necessary during normal takeoff. Similarly, at the time of landing, the aircraft 10 descends (vertically landing) by the thrust of the flight platform 20, so that it does not consume as much fuel as is required at the time of normal landing. Therefore, the aircraft 10 does not need to perform takeoff and landing that requires thrust with its own propulsion device, so that the propulsion device can be miniaturized.

Further, since the electric fan 23, which is the source of thrust of the flight gantry 20, is housed in the gantry main body 21, the gantry main body 21 is in a flat state. Therefore, since the electric fan 23 does not become an obstacle to the aircraft 10, the aircraft 10 can be safely taken off and landed on the flight platform 20.

Further, since a plurality of electric fans 23 are provided, redundancy due to a failure of the electric fans 23 can be ensured.

Further, since the electric fans 23 are arranged in a grid pattern, the electric fans 23 can be efficiently provided in a dense state.

Further, since the electric fan 23 can be tilted with respect to the gantry main body 21, the flight gantry 20 can be made to fly forward without tilting the flight gantry 20. That is, the flight platform 20 can be made to fly forward while the mounting surface 22 is maintained horizontally. Therefore, it is possible to prevent the aircraft 10 mounted on the mounting surface 22 from falling. Since the electric fan 23 can be tilted for each movable fan unit 24B, the control can be simplified as compared with the case where the tilt control is executed for each electric fan 23.

Further, since the mounting surface 22 may be provided on the gantry main body 21 by the cover member 25 mounted on the electric fan 23, the shape of the mounting surface 22 can be easily changed by attaching / detaching the cover member 25.

[Second Embodiment]
The present embodiment is different from the first embodiment in that the arresting wire 30 is provided, and the other configurations are the same. Therefore, the same components are designated by the same reference numerals and the description thereof will be omitted.

As shown in FIG. 17, the flight gantry 20 includes an arresting wire 30 that captures the aircraft 10.

As shown in FIG. 18, the arresting wire 30 is arranged at the rear of the flight platform 20 and is connected to a first winch portion 32 having different ends.
The first winch portion 32 is housed in the lower part of the mounting surface 22 and can wind or send out the arresting wire 30.

The arresting wire 30 extending from the first winch portion 32 is guided in an annular shape by the pulley 33. The pulley 33 is connected to the flight platform 20 via a universal joint, and its orientation can be freely changed.

As shown in FIGS. 18 and 19, a small wing 31 is attached to the arresting wire 30. As a result, as shown in FIG. 20, the arresting wire 30 can be levitated at a position where the arresting hook 11 of the aircraft 10 can be easily hooked.

Further, as shown in FIG. 18, two lead-in wires 40 are connected to the arresting wire 30. One end of each lead-in wire 40 is connected to the arresting wire 30, and the other end is connected to the second winch portion 42 via the pulley 43. The second winch portion 42 is housed in the lower part of the mounting surface 22 and can wind up or send out the lead-in wire 40.

The arresting wire 30 configured as described above operates as follows.
As shown in FIG. 20, when the aircraft 10 approaches from behind the flight gantry 20, the arresting wire 30 and the flight gantry 20 are released from being fixed, and the arresting wire 30 is sent out by the first winch portion 32 to provide wings. The lift of 31 raises the arresting wire 30. At this time, the arresting wire 30 is disengaged from the two pulleys 33 arranged rearward.
The aircraft 10 approaches the flight gantry 20 with the legs retracted in the airframe and the arresting hook 11 lowered.

As shown in FIGS. 21 to 23, when the arresting hook 11 is hooked on the arresting wire 30 and the aircraft 10 and the flight platform 20 become constant speed, the first winch portion 32 winds up the arresting wire 30. , The aircraft 10 is attracted to the flight gantry 20 (or the flight gantry 20 is attracted to the aircraft 10).
The legs of the aircraft 10 are lowered while the first winch portion 32 winds up the arresting wire 30.

When the arresting wire 30 is further wound, the main landing gear of the aircraft 10 is located on the flight platform 20 as shown in FIGS. 24 and 25. When the second winch portion 42 winds up the pull-in wire 40 in this state, the arresting wire 30 is pulled to the rear end of the flight gantry 20 as shown in FIGS. 26 and 27, and the aircraft 10 is mounted on the mounting surface 22 together with the arresting wire 30. Placed in the proper position above.

According to this embodiment, the following effects are obtained.
Since the arresting wire 30 connected to the gantry main body 21 is provided, the aircraft 10 provided with the arresting hook 11 can be captured in the air.

Further, since the first winch portion 32 for winding or sending out the arresting wire 30 is provided, the captured aircraft 10 can be attracted to the flight gantry 20.

Further, since the arresting wire 30 has wings 31, the arresting wire 30 can be levitated at a position where the arresting hook 11 can be easily hooked when the aircraft 10 is captured.

In the first and second embodiments described above, as shown in FIG. 28, the vertical cross section of the gantry main body 21 may have a wing shape. This makes it possible to reduce the air resistance that may occur in the flight platform 20.

Each embodiment described as described above is grasped as follows, for example.
That is, the flight pedestal (20) according to one aspect of the present disclosure includes a gantry main body (21) having a mounting surface (22) on which an aircraft (10) can be mounted, a plurality of electric fans (23), and a plurality of electric fans (23). The plurality of electric fans (23) are housed in the gantry main body (21).

The flight pedestal (20) according to this embodiment includes a gantry main body (21) having a mounting surface (22) on the upper surface on which an aircraft (10) can be mounted, and a plurality of electric fans (23). Since the electric fan (23) is housed in the gantry main body (21), the flight gantry (20) can take off vertically with the aircraft (10) mounted by the thrust of the electric fan (23). Further, the aircraft (10) accelerates and advances together with the flight platform (20) until the aircraft (10) has lift, and if the lift of the aircraft (10) exceeds the weight of the aircraft (10), the aircraft (10) has its own propulsion device (10). For example, a jet engine or an electric fan) can fly away from the flight platform (20). This allows the aircraft (10) to take off and be ready to fly without a runway. Further, since the aircraft (10) ascends (vertically takes off) by the thrust of the flight platform (20) instead of its own thrust, it does not consume as much fuel as necessary during normal takeoff. Similarly, at the time of landing, the aircraft (10) descends (vertically landing) by the thrust of the flight platform (20), so that it does not consume as much fuel as necessary at the time of normal landing.
Further, since the electric fan (23), which is the source of thrust of the flight gantry (20), is housed in the gantry main body (21), the gantry main body (21) is in a flat state. Therefore, since the electric fan (23) does not become an obstacle to the aircraft (10), the aircraft (10) can be safely taken off and landed on the flight platform (20).
Further, since a plurality of electric fans (23) are provided, redundancy due to a failure of the electric fan (23) can be ensured.

Further, in the flight pedestal (20) according to one aspect of the present disclosure, the electric fan (23) can be tilted with respect to the gantry main body (21).

In the flight pedestal (20) according to this embodiment, since the electric fan (23) can be tilted with respect to the gantry main body (21), the flight gantry (20) can be advanced without tilting the flight gantry (20). Can be flown. That is, the flight platform (20) can be made to fly forward while the mounting surface (22) is maintained horizontally. Therefore, it is possible to prevent the aircraft (10) mounted on the mounting surface (22) from falling.

Further, in the flight platform (20) according to one aspect of the present disclosure, the electric fans (23) are arranged in a grid pattern.

In the flight pedestal (20) according to this aspect, since the electric fans (23) are arranged in a grid pattern, the electric fans (23) can be efficiently provided in a dense state.

Further, in the flight platform (20) according to one aspect of the present disclosure, one fan unit (24) is composed of four electric fans (23) arranged in a grid pattern, and the electric fan (23) is , The fan unit (24) can be tilted.

In the flight gantry (20) according to this aspect, one fan unit (24) is composed of four electric fans (23) arranged in a grid pattern, and the electric fan (23) is for each fan unit (24). Since the tilt is possible, the control can be simplified as compared with the case where the tilt control is executed for each electric fan (23).

Further, in the flight pedestal (20) according to one aspect of the present disclosure, the mounting surface (22) is provided on the pedestal main body (21) by the cover member (25) mounted on the electric fan (23). Has been done.

In the flight pedestal (20) according to this embodiment, since the mounting surface (22) is provided on the gantry main body (21) by the cover member (25) mounted on the electric fan (23), the cover member ( The shape of the mounting surface (22) can be easily changed by attaching / detaching 25).
It can also be used as a passage for moving the aircraft (10) on the flight platform (20).

Further, in the flight pedestal (20) according to one aspect of the present disclosure, the gantry main body (21) has a wing-shaped vertical cross section.

Since the flight pedestal (20) according to this embodiment has a wing-shaped vertical cross section, it is possible to reduce the air resistance that may occur in the flight gantry (20) during flight.

Further, the flight pedestal (20) according to one aspect of the present disclosure includes an arresting wire (30) connected to the gantry main body (21).

Since the flight pedestal (20) according to this embodiment includes an arresting wire (30) connected to the gantry main body (21), the aircraft (10) provided with the arresting hook (11) is captured in the air. can.

Further, the flight platform (20) according to one aspect of the present disclosure includes a winch portion (32) for winding or sending out the arresting wire (30).

Since the flight pedestal (20) according to this embodiment includes a winch portion (32) for winding or sending out the arresting wire (30), the captured aircraft (10) can be attracted to the flight gantry (20). ..

Further, in the flight platform (20) according to one aspect of the present disclosure, the arresting wire (30) has wings (31).

In the flight platform (20) according to this embodiment, since the arresting wire (30) has wings (31), the arresting hook (11) can be easily hooked when the aircraft (10) is captured. The arresting wire (30) can be levitated.

Further, the flight pedestal (20) according to one aspect of the present disclosure includes a control unit for controlling the electric fan (23), and the fan units (24) are arranged in a grid pattern and four are arranged at four corners. The posture is controlled by the control unit controlling the rotation speed of each of the electric fans (23) of the fan unit (24).

The flight pedestal (20) according to this aspect includes a control unit for controlling an electric fan (23), the fan units (24) are arranged in a grid pattern, and each of the four fan units (24) arranged at the four corners. Since the attitude is controlled by the control unit controlling the rotation speed of the electric fan (23), the fan units (24) arranged at the four corners are combined with the fan unit (24) dedicated to the attitude control of the flight platform (20). By doing so, it is possible to avoid complicated control. The "attitude control" referred to here is, for example, control of the pitch, roll, and yaw of the flight platform (20).

Further, in the flight pedestal (20) according to one aspect of the present disclosure, the control unit has a takeoff mode in which the aircraft (10) rises while being mounted on the mounting surface (22), and the mounting surface (22). ), An acceleration flight mode in which the aircraft (10) accelerates and advances until it has a lift that can support its own weight, and a landing mode in which the aircraft (10) descends while being mounted on the mounting surface (22). ,I do.

Further, the takeoff and landing support system according to one aspect of the present disclosure includes the above-mentioned flight platform (20) and the aircraft (10) having a propulsion device, and the flight platform (20) is the aircraft (10). Is mounted on the mounting surface (22) and ascended, and the flight platform (20) accelerates and advances with the aircraft (10) on which the propulsion device is started, and the aircraft (10) Departs from the aircraft (10) when it has lift that can support its own weight.

The takeoff and landing support system according to this embodiment includes the above-mentioned flight platform (20) and an aircraft (10) having a propulsion device, and the flight platform (20) mounts the aircraft (10) on the mounting surface (22). The aircraft (10) starts the propulsion device after ascending the flight gantry (20), and the flight gantry (20) accelerates and advances with the aircraft (10) mounted on the aircraft. Since (10) separates from the aircraft (10) when it has a lift that can support its own weight, the aircraft (10) is capable of vertical takeoff and does not consume as much fuel as required during normal takeoff.
Further, since the aircraft (10) does not need to perform takeoff requiring thrust by its own propulsion device, it is possible to realize miniaturization of the propulsion device.

Further, in the takeoff and landing support system according to one aspect of the present disclosure, the flight platform (20) approaches the flying aircraft (10) and mounts the aircraft (10) on the mounting surface (22). Then, the aircraft (10) stops the propulsion device while being mounted on the mounting surface (22), and the flight platform (20) puts the aircraft (10) on the mounting surface (22). It descends with it mounted.

In the takeoff and landing support system according to this embodiment, the flight platform (20) approaches the flying aircraft (10) and mounts the aircraft (10) on the mounting surface (22), and the aircraft (10) is mounted. The propulsion device is stopped while mounted on the surface (22), and the flight platform (20) descends after the propulsion device of the aircraft (10) is stopped, so that the aircraft (10) can make a vertical landing. Does not consume as much fuel as needed during a normal landing.
Further, since the aircraft (10) does not need to make a landing that requires thrust by its own propulsion device, the propulsion device can be miniaturized.

Further, the operation method of the flight platform (20) according to one aspect of the present disclosure includes a step of ascending with the aircraft (10) mounted on the mounting surface (22) and mounting on the mounting surface (22). It includes a step of accelerating and advancing until the aircraft (10) has a lift that can support its own weight, and a step of descending with the aircraft (10) mounted on the mounting surface (22).

Further, the operation method of the takeoff and landing support system according to one aspect of the present disclosure includes a step in which the flight pedestal (20) rises with the aircraft (10) mounted on the mounting surface (22), and the flight pedestal. (20) accelerates and advances with the aircraft (10) on which the propulsion device has been started, and leaves the aircraft (10) when the aircraft (10) has lift that can support its own weight. Including steps.

10 Aircraft 11 Arresting hook 20 Flight mount 21 Mount body 22 Mounting surface 23 Electric fan 24 Fan unit 24A Fixed fan unit 24B Movable fan unit 25 Cover member 30 Arresting wire 31 Wing 32 First winch 33 Pulley 40 Pull-in wire 42 No. 2 winch 43 pulley

Claims (15)

A gantry body with a mounting surface on the upper surface on which an aircraft can be mounted,
With multiple electric fans
Equipped with
The plurality of electric fans are flight pedestals housed in the gantry main body. The flight pedestal according to claim 1, wherein the electric fan can be tilted with respect to the gantry main body. The flight platform according to claim 1 or 2, wherein the electric fan is arranged in a grid pattern. One fan unit is composed of the four electric fans arranged in a grid pattern.
The flight platform according to claim 2 or 3, wherein the electric fan can be tilted for each fan unit. The flight pedestal according to any one of claims 1 to 4, wherein the mounting surface is provided on the gantry main body by a cover member mounted on the electric fan. The flight pedestal according to any one of claims 1 to 5, wherein the gantry main body has a wing shape in a vertical cross section. The flight pedestal according to any one of claims 1 to 6, further comprising an arresting wire connected to the gantry body. The flight platform according to claim 7, further comprising a winch portion for winding or sending out the arresting wire. The flight platform according to claim 7 or 8, wherein the arresting wire has wings. A control unit for controlling the electric fan is provided.
The fan units are arranged in a grid pattern.
The flight platform according to any one of claims 1 to 9, wherein the attitude is controlled by the control unit controlling the rotation speed of each of the electric fans of the four fan units arranged at the four corners. The control unit includes a takeoff mode in which the aircraft is mounted on the mounting surface and ascends, and an accelerated flight mode in which the aircraft mounted on the mounting surface accelerates and advances until it has a lift that can support its own weight. The flight platform according to claim 10, wherein the landing mode in which the aircraft descends while being mounted on the mounting surface is performed. The flight platform according to any one of claims 1 to 11.
With the aircraft having a propulsion device,
Equipped with
The flight pedestal rises with the aircraft mounted on the mounting surface,
The flight pedestal is a takeoff and landing support system that accelerates and advances with the aircraft on which the propulsion device has been started, and separates from the aircraft when the aircraft has lift that can support its own weight. The flight pedestal approaches the flying aircraft and mounts the aircraft on the mounting surface.
The aircraft is mounted on the mounting surface and the propulsion device is stopped.
The takeoff and landing support system according to claim 12, wherein the flight platform descends with the aircraft mounted on the mounting surface. The method for operating a flight platform according to any one of claims 1 to 11.
The step of ascending with the aircraft mounted on the mounting surface,
A step of accelerating and advancing until the aircraft mounted on the mounting surface has lift that can support its own weight.
The step of descending with the aircraft mounted on the mounting surface,
How to operate the flight platform including. The operation method of the takeoff and landing support system according to claim 12.
A step in which the flight platform rises with the aircraft mounted on the mounting surface.
A step of accelerating and advancing the flight platform with the aircraft on which the propulsion device has been started, and leaving the aircraft when the aircraft has lift to support its own weight.
How to operate the takeoff and landing support system including.

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