JP7506368B2 - Aircraft take-off and landing system, take-off and landing gear for aircraft, and aircraft - Google Patents

Description

The present invention relates to an aircraft takeoff and landing system, an aircraft takeoff and landing device, and an aircraft.

Conventionally, flying objects such as drones and unmanned aircraft that are remotely or automatically controlled to fly have generally taken off and landed on flat surfaces, such as a dedicated landing pad, the ground, the top of a vehicle, or the roof of a building (see, for example, Patent Documents 1 and 2). However, these general flying objects have had the problem that they take a long time to land because of the so-called ground effect, which can cause control to become unstable or there is a risk of them tipping over. Another problem is that a sufficiently large space is required for safe takeoff and landing.

There is also a system for capturing and landing an aircraft in the air, rather than on the ground, in which an arm with a hook at the end is attached to the aircraft so that it extends upward, and which has a rail suspended horizontally by a crane, a shuttle that is movable along the rail, and a cable that is suspended from the shuttle and stretched so that it extends vertically to the rail. The aircraft flies along the rail below the rail, and by touching the aircraft's arm to the cable, as the aircraft moves, the position where the arm touches the cable shifts upward on the arm, so that the hook gets caught on the cable and the aircraft can be captured (see, for example, Patent Document 3). However, with this system, the aircraft cannot take off in the landed state, so it is necessary to first detach the aircraft's hook from the cable and reset the aircraft to a state where it can take off, which makes it difficult to take off smoothly.

In order to solve these problems, the inventors have developed a takeoff and landing system for an aircraft, which has a pair of rails arranged side by side with a gap between them, and an aircraft with a hanging part at the top that can be inserted between the rails, and with the hanging part inserted between the rails, the aircraft can be suspended at a predetermined landing position on each rail, and the aircraft suspended at the landing position can take off (see, for example, Patent Document 4). With this system, the aircraft is suspended and landed, so the influence of ground effect can be reduced, and the aircraft can take off and land smoothly even in a relatively narrow space. However, this system requires a place to install the rails, so there are places where it is not suitable for use.

There is an aircraft takeoff and landing system that can be used in places where rails cannot be installed and that suspends and lands an aircraft. The system has a hanging body that is suspended from a specified location and has a connecting part at the bottom end, and an aircraft that has an anchor part at the top that can be connected to the connecting part of the hanging body, and the anchor part is connectable to the connecting part from below (see, for example, Non-Patent Document 1). In this system, when the aircraft is to land, the anchor part is connected to the connecting part from below, and when the aircraft is to take off, the anchor part is detached from the connecting part, and the aircraft is dropped and then taken off.

JP 2019-089461 A JP 2018-190362 A U.S. Pat. No. 9,010,683 Patent No. 6789558

Musa Galimov, Roman Fedorenko and Alexander Klimchik, “UAV Positioning Mechanisms in Landing Stations: Classification and Engineering Design Review”, Sensors, 2020, 20, 3648, p.15, Figure 23

However, the takeoff and landing system described in Non-Patent Document 1 has problems in that the direction during takeoff and landing is limited to the up and down directions, the range in which the connecting part and the anchor part can be connected is narrow, so the aircraft needs to be guided almost pinpoint-wise to the connecting range during landing, and the aircraft needs to be carefully controlled during takeoff to prevent it from crashing.

The present invention was made with a focus on these issues, and aims to provide an aircraft takeoff and landing system, an aircraft takeoff and landing device, and an aircraft that can be used in places where rails cannot be installed and can take off and land smoothly in a relatively short time.

In order to achieve the above-mentioned object, the aircraft take-off and landing system of the present invention comprises a support part, a hanging body that is elongated and extended downward with its upper end supported by the support part and has an engagement part at its lower end, and an aircraft having a detachable part at its upper part that is capable of engaging with the engagement part of the hanging body, wherein the aircraft is configured to be able to release the detachable part from the engagement part by moving upward or sideways from a state in which the detachable part and the engagement part are engaged, and the hanging body comprises an elongated pole, and the engagement part is movable in any horizontal direction and the upper end is rotatably attached to the support part . Alternatively, the aircraft take-off and landing system of the present invention comprises a support part, a hanging body that is elongated and extended downward with its upper end supported by the support part and has an engagement part at its lower end, and an aircraft having a detachable part at its upper part that is capable of engaging with the engagement part of the hanging body, wherein the aircraft is configured to be able to release the detachable part from the engagement part by moving upward or sideways from a state in which the detachable part and the engagement part are engaged, and the hanging body and/or the detachable part are configured to be able to absorb impact when the detachable part collides with the hanging body.

The take-off and landing device for an aircraft of the present invention is a take-off and landing device for an aircraft for landing the aircraft, comprising a support part and a hanging body that is elongated and extended downward with its upper end supported by the support part and has an engagement part at its lower end, the aircraft having a detachable part at its upper part that is capable of engaging with the engagement part of the hanging body , the hanging body consisting of an elongated pole, the engagement part being movable in any horizontal direction and the upper end being rotatably attached to the support part, and configured such that when the aircraft moves upward or sideways from a state in which the detachable part and the engagement part are engaged, the detachable part can be released from the engagement part. Alternatively, the take-off and landing device for an aircraft of the present invention is a take-off and landing device for an aircraft for landing the aircraft, comprising a support part and a hanging body that is elongated and extends downward with its upper end supported by the support part and has an engagement part at its lower end, the aircraft having a detachable part at its upper part that is capable of engaging with the engagement part of the hanging body, the hanging body being configured to absorb impact when the detachable part collides with the hanging body, and being configured such that when the aircraft moves upward or sideways from a state in which the detachable part and the engagement part are engaged, the detachable part can be released from the engagement part.

The flying body of the present invention is an elongated flying body that is supported at its upper end and extends downward, and takes off and lands using a hanging body having an engagement portion at its lower end, and has a detachable portion at its upper part that is capable of engaging with the engagement portion of the hanging body, and is configured to be able to release the detachable portion from the engagement portion by moving upward or sideways from a state in which the detachable portion and the engagement portion are engaged , and the detachable portion is configured to be able to absorb impact when the detachable portion collides with the hanging body .

The aircraft takeoff and landing system of the present invention can be configured by combining the aircraft takeoff and landing device of the present invention with the aircraft of the present invention. In this case, the suspended body of the aircraft takeoff and landing device of the present invention corresponds to the suspended body of the aircraft takeoff and landing system of the present invention, and the aircraft of the present invention corresponds to the aircraft of the aircraft takeoff and landing system of the present invention. Therefore, the aircraft takeoff and landing device of the present invention and the aircraft of the present invention have the action and effect of the corresponding configuration of the aircraft takeoff and landing system of the present invention shown below.

In the aircraft takeoff and landing system according to the present invention, the aircraft is preferably a drone or unmanned aeroplane that can fly by remote control or automatic control. The aircraft takeoff and landing system according to the present invention can take off and land the aircraft as follows. That is, when landing, the aircraft is flown toward the bottom of the hanging body that is supported at its upper end by a support part and extends downward, and the attachment/detachment part provided at the top of the aircraft is engaged with the engagement part of the hanging body. This allows the aircraft to land while suspended from the hanging body. At this time, by arranging the hanging body so that there is sufficient space below the aircraft, the influence of the ground effect can be reduced to a level that can be almost ignored. In addition, since there is almost no influence of the ground effect, the aircraft can be landed stably even in a relatively narrow space. When taking off, the aircraft can be moved upward or to the side.

As a configuration of the detachable part and the engaging part, for example, the detachable part may be configured to engage with the engaging part by moving toward the engaging part while in contact between the upper end of the suspended body and the engaging part. In this case, the flying body is flown to bring the detachable part into contact between the upper end of the suspended body and the engaging part, and in that state, the flying body is moved so that the detachable part moves toward the engaging part of the suspended body, thereby engaging the detachable part and the engaging part. In this way, it is sufficient to guide the flying body so that the detachable part comes into contact between the upper end of the suspended body and the engaging part, which makes it easier to control the flying body compared to guiding the flying body almost at a pinpoint, and allows it to land smoothly in a relatively short time.

The detachment part may be configured to be released from the engagement part by moving from the engagement part toward the upper end along the extension direction of the suspended body, or may be configured to be released from the engagement part by moving laterally toward a direction within a predetermined angle range relative to the extension direction of the suspended body. In these cases, the flying object can be moved actively while taking off safely. Also, the flying object can be taken off smoothly in a relatively short time by simply moving it actively.

The detachable part may be configured with, for example, a magnet, hook-and-loop fastener, suction cup, etc., so that it engages simply by contacting it with the engaging part. The detachable part may also be configured with a gripper that can adapt to the shape of an object and grasp the object simply by contacting it. In these cases, the flying object can be easily taken off by simply moving it upward or to the side so as to move away from the suspended body when the detachable part and the engaging part are engaged. This allows for smooth takeoff and landing in a relatively short time.

The aircraft takeoff and landing system according to the present invention can be used even in places where rails cannot be installed, so long as the suspended body can be placed there. Furthermore, the aircraft can land no matter which direction it approaches the suspended body from. For this reason, the suspended body may be installed in any location as long as there is space at least below and to the side of the engagement part. The suspended body may be installed, for example, on the ceiling or under the eaves of a factory, house, or building, or may be suspended by a crane, etc.

The aircraft takeoff and landing system according to the present invention can be suitably used, for example, when attaching and transporting luggage to the bottom of the aircraft. When the aircraft is suspended from the suspension body, there is space below the aircraft, making it easy to attach luggage to the bottom of the aircraft and to remove luggage attached to the bottom of the aircraft. In addition, when the aircraft is suspended from the suspension body, it is also possible to supply power and transmit and receive data in a non-contact manner. In addition, the system may be configured to be able to supply a specific object, substance, energy, etc., such as liquid, pesticides, luggage, batteries, or electricity, to the aircraft via the suspension body and the detachment part.

In the aircraft takeoff and landing system according to the present invention, when the suspended body is made of a long and thin pole, the engaging portion is movable in any horizontal direction, and the upper end portion is rotatably attached to the support portion, even if the detachable portion collides between the upper end portion of the suspended body and the engaging portion during landing, the suspended body rotates around the upper end portion in the collision direction, so that the impact during the collision can be softened. This makes it possible to prevent the suspended body, the detachable portion, etc. from being damaged by the collision. In addition, due to the biasing force of the aircraft during the collision, the detachable portion that collides with the suspended body moves toward the engaging portion along the length direction of the suspended body, and the detachable portion can be engaged with the engaging portion. This allows the aircraft to land on the suspended body without being damaged while being given momentum. The suspended body may be attached to the support portion via a universal joint, for example.

Furthermore, in the aircraft takeoff and landing system according to the present invention, even if the suspended body and/or the detachable part are configured to be capable of absorbing the impact when the detachable part collides with the suspended body, the detachable part can be prevented from colliding with the suspended body and damaging the suspended body, detachable part, etc., during landing. Furthermore, when the detachable part collides with the suspended body, the aircraft or the suspended body can be prevented from bouncing back, allowing the aircraft to land more reliably. As a configuration capable of absorbing the impact when colliding, for example, it is preferable to form the suspended body or the detachable part from a flexible material, or to provide a damper in the suspended body or the detachable part.

In addition, in the aircraft takeoff and landing system according to the present invention, the detachable part may be arranged to be deformable between a protruding state in which it extends upward from the aircraft and a stored state in which it protrudes less upward from the aircraft than in the protruding state. In this case, by putting the detachable part in the protruding state when landing, it is possible to make landing easier. Also, by putting the detachable part in the stored state during flight, it is possible to prevent the detachable part from colliding with or getting caught on something during flight.

The present invention provides an aircraft takeoff and landing system, an aircraft takeoff and landing device, and an aircraft that can be used in places where rails cannot be installed and can take off and land smoothly in a relatively short time.

1 is a side view showing a state in which an aircraft takeoff and landing system according to an embodiment of the present invention is in use. 1A is a side view showing an embodiment of the aircraft takeoff and landing system of the present invention, in which a suspended body is installed on (a) a tripod-type stand and (b) a mobile body moving on the ground. 1A and 1B are side views showing the state in which a suspended body is installed on an aircraft takeoff and landing system according to an embodiment of the present invention, respectively. 1A and 1B are a plan view and a side view showing a first modified example of an engagement portion and an attachment/detachment mechanism of an aircraft takeoff and landing system according to an embodiment of the present invention. Showing a second modified example of the engagement portion and detachment mechanism of an aircraft takeoff and landing system of an embodiment of the present invention, (a) a plan view of the engagement portion with each finger portion open, (b) a side view of the aircraft and suspended body showing the aircraft inserted between each finger portion, (c) a plan view of the engagement portion in a state where the aircraft is gripped, and (d) a side view of the aircraft and suspended body in a state where the aircraft is gripped. 13A and 13B are plan and side views showing a third modified example of an engagement portion and an attachment/detachment mechanism of an aircraft takeoff and landing system according to an embodiment of the present invention. 13A and 13B are plan and side views showing a fourth modified example of an engagement portion and an attachment/detachment mechanism of an aircraft takeoff and landing system according to an embodiment of the present invention. 13A and 13B are plan and side views showing a fifth modified example of an engagement portion and a detachment mechanism of an aircraft takeoff and landing system according to an embodiment of the present invention. 13A and 13B are plan and side views showing a sixth modified example of an engagement portion and an attachment/detachment mechanism of an aircraft takeoff and landing system according to an embodiment of the present invention. 2 is a side view for explaining the configuration of the engagement portion and the attachment/detachment mechanism of the aircraft takeoff and landing system according to an embodiment of the present invention. FIG. 1 is a perspective view showing a state in which an aircraft takeoff and landing system according to an embodiment of the present invention is used as a takeoff and landing system for an underwater vehicle. FIG. 1 is a plan view of an aircraft takeoff and landing system according to an embodiment of the present invention, which utilizes a pole extending vertically upward; (a) is a plan view of the pole; (b) is an oblique view showing the state of use; and (c) is a plan view of the aircraft.

Hereinafter, an embodiment of the present invention will be described with reference to the drawings.
1 to 11 show an aircraft takeoff and landing system, an aircraft takeoff and landing gear, and an aircraft according to an embodiment of the present invention.
As shown in FIG. 1 , an aircraft takeoff and landing system 10 according to an embodiment of the present invention has a support unit 11 , a suspended body 12 , and an aircraft 13 .

As shown in FIG. 1, the support 11 is made of a member that extends laterally, and is arranged with a space at least downward and partially to the side. The hanging body 12 is made of a long, thin, round bar-shaped pole, and is supported at its upper end by the support 11, and is provided so as to extend downward. In the specific example shown in FIG. 1, the support 11 is made of a rod-shaped member, and one end 11a is attached to a column-shaped part 2 that extends upward from a base 1 installed on the ground. The hanging body 12 is also attached to the other end 11b of the support 11.

The suspended body 12 is not limited to the configuration shown in FIG. 1, and may be installed in any location as long as there is space at least partially below and to the sides. For this reason, the suspended body 12 may be installed, for example, under the ceiling or eaves of a factory, house, or building, or may be suspended by a crane or the like. In these cases, the ceiling, eaves, or crane arm form the support part 11. As shown in FIG. 2 and FIG. 3, the suspended body 12 may be installed via the support part 11 on a tripod stand 3, a moving body 4 that moves on the ground, a ship 5, an airplane 6, or the like. In these cases, the parts that form the moving body 3, the stand 4, the ship 5, the airplane 6, or the like may form the support part 11.

As shown in FIG. 1, the suspended body 12 has an engagement portion 12a at its lower end. The upper end of the suspended body 12 is rotatably attached to the support portion 11 via a universal joint 12b. This allows the engagement portion 12a of the suspended body 12 to move in any horizontal direction. In one specific example, the engagement portion 12a is made of a sphere having a diameter larger than the diameter of the other parts of the suspended body 12. The support portion 11 and the suspended body 12 form an aircraft takeoff and landing device for landing the aircraft 13.

The flying object 13 has a detachable part 21 at its top that extends upward. The detachable part 21 has an arm 21a that extends upward from the flying object 13, and an attachment/detachment mechanism 21b provided at the tip of the arm 21a. In one specific example, the attachment/detachment mechanism 21b has a dogleg shape that opens laterally so as to sandwich the hanging object 12 above the engagement part 12a.

The detachment part 21 is configured to move toward the engagement part 12a while in contact between the upper end of the suspended body 12 and the engagement part 12a, so that the detachment mechanism 21b engages with the engagement part 12a. This allows the flying vehicle 13 to land while suspended from the suspended body 12. Note that the detachment part 21 may also be configured to move toward the engagement part 12a while in contact only with the engagement part 12a, so that the detachment mechanism 21b engages with the engagement part 12a.

The detachment unit 21 is configured such that, with the detachment mechanism 21b engaged with the engagement unit 12a, the detachment mechanism 21b is released from the engagement unit 12a by moving laterally from the engagement unit 12a toward the upper end along the extension direction of the suspended body 12, or toward a direction within a predetermined angle range relative to the extension direction of the suspended body 12. This allows the flying object 13 to move upward or sideways, making it possible for it to take off. In this way, the detachment unit 21 of the flying object 13 is detachable from the engagement unit 12a.

In the example shown in FIG. 1, the flying object 13 is a drone, but it may be any flying object, such as an unmanned aerial vehicle. The flying object 13 may also be capable of flying by remote control or automatic control.

The aircraft takeoff and landing system 10 may have a configuration of the engagement portion 12a and the detachment mechanism 21b other than that shown in FIG. 1. For example, as shown in FIG. 4, the engagement portion 12a has a plurality of elongated arms 31 extending radially to the side, and the detachment portion 21 may have a shape that makes it easy for the detachment mechanism 21b to be caught on the upper portion of the engagement portion 12a when the arm 1b enters the back of the adjacent arm portion 31. For example, as shown in FIG. 4, the detachment mechanism 21b may have a dogleg shape so as to sandwich the hanging body 12 at the upper portion of the engagement portion 12a, or may have a shape with a width or diameter greater than the width at the back of the adjacent arm portion 31. The shape of the engagement portion 12a and the shape of the detachment mechanism 21b may be interchanged.

Also, as shown in FIG. 5, the engaging portion 12a may be composed of a gripper that can be gripped by opening and closing two fingers 32, and the detachment mechanism 21b may have a shape larger than the space when the fingers 32 of the gripper are closed. In this case, it is preferable that when the arm 21a of the detachment portion 21 enters between the two fingers 32 of the gripper, the fingers 32 are closed by the biasing force of the arm 21a, and when the arm 21a presses the tip of each finger 32 from inside the closed fingers 32, each finger 32 is opened. Also, the shape of the engaging portion 12a and the shape of the detachment mechanism 21b may be interchanged.

The aircraft takeoff and landing system 10 may also be configured to engage simply by bringing the detachment mechanism 21b into contact with the engagement portion 12a. In this case, for example, as shown in FIG. 6, the engagement portion 12a and the detachment mechanism 21b may each be made of a hook and loop of a hook-and-loop fastener so that they can be attached to each other. The engagement portion 12a may be a loop of a hook-and-loop fastener, and the detachment mechanism 21b may be a hook-and-loop fastener. As shown in FIG. 7, the engagement portion 12a may be a cylindrical magnet that is rotatable around a central axis and has alternating north and south poles on its side along the direction of rotation, and the detachment mechanism 21b may be a magnet that has alternating north and south poles on its side along the circumferential direction of the arm 21a.

Also, as shown in FIG. 8, the engaging portion 12a may be cylindrical and have a plurality of suction cups 33, suction pads, or non-contact suction pads on its side, and the attachment/detachment mechanism 21b may be a plate-like body having a curved surface 34 along the side of the engaging portion 12a, and may be provided rotatably along the circumferential direction of the arm 21a with the curved surface 34 facing to the side. The attachment/detachment mechanism 21b may be attached to the arm 21a via a spring.Also, as shown in FIG. 9, the engaging portion 12a may be a gripper that can adapt to the shape of an object and grasp the object simply by contacting the object.

In this way, the aircraft takeoff and landing system 10 only needs to be able to engage the engagement portion 12a with the detachment mechanism 21b, and to be able to easily release the detachment mechanism 21b from the engagement portion 12a when the aircraft 13 takes off. For this reason, the configuration of the engagement portion 12a and the configuration of the detachment mechanism 21b may be interchanged, and as shown in FIG. 10, when the engagement portion 12a is female, the detachment mechanism 21b is male, and when the engagement portion 12a is male, the detachment mechanism 21b is female.

Next, the operation will be described.
The flying body takeoff and landing system 10 can take off and land the flying body 13 as follows. That is, when landing, the flying body 13 is flown toward the lower side of the suspended body 12, and the detachable part 21 provided on the upper part of the flying body 13 is brought into contact between the upper end of the suspended body 12 and the engagement part 12a. At this time, even if the detachable part 21 and the suspended body 12 collide, the suspended body 12 rotates in the collision direction by the universal joint 12b, so that the impact at the time of the collision can be softened. Therefore, as long as the impact is within the range of the impact that can be absorbed by the rotational movement of the suspended body 12, the detachable part 21 may be caused to collide with the suspended body 12 while the flying body 13 is in a state where momentum is applied thereto.

After the hanging body 12 and the detachment part 21 are brought into contact with each other, the flying object 13 can be moved toward the engagement part 12a in this state, thereby engaging the detachment mechanism 21b with the engagement part 12a. In this way, the flying object 13 can land while suspended from the hanging body 12. Also, when the detachment part 21 collides with the hanging body 12 while the flying object 13 is in a state of being given momentum, the detachment part 21 that collides with the hanging body 12 moves toward the engagement part 12a along the length direction of the hanging body 12 due to the biasing force of the flying object 13 at the time of the collision, so that the detachment mechanism 21b can be engaged with the engagement part 12a. As a result, the flying object 13 can land while suspended from the hanging body 12 while being given momentum, without being damaged.

By positioning the suspended body 12 so that there is sufficient space below the aircraft 13, the aircraft takeoff and landing system 10 can reduce the influence of ground effect to a level that can be almost ignored. Furthermore, because there is almost no influence of ground effect, the aircraft 13 can land stably even in a relatively narrow space. Furthermore, when landing, the aircraft 13 only needs to be guided so that the detachment part 21 comes into contact between the upper end of the suspended body 12 and the engagement part 12a, which makes it easier to control the aircraft 13 compared to guiding the aircraft 13 almost to a pinpoint, allowing it to land smoothly in a relatively short time.

When the flying object 13 is to take off, the attachment/detachment mechanism 21b can be released from the engagement portion 12a by moving the flying object 13 upward or to the side. Therefore, the flying object 13 can be made to take off smoothly and safely in a relatively short time simply by actively moving it.

The aircraft takeoff and landing system 10 can be used in locations where rails cannot be installed, as long as the suspended body 12 can be placed. In addition, the aircraft 13 can land on the suspended body 12 regardless of the direction from which it approaches it.

The aircraft takeoff and landing system 10 can be suitably used, for example, when attaching and transporting luggage to the bottom of the aircraft 13. When the aircraft 13 is suspended from the hanging body 12, there is space below the aircraft 13, so that luggage can be easily attached to the bottom of the aircraft 13 and luggage attached to the bottom of the aircraft 13 can be easily removed. In addition, when the aircraft 13 is suspended from the hanging body 12, it is also possible to supply power and transmit and receive data in a non-contact manner. In addition, a specific object, substance, energy, etc., such as liquid, pesticide, luggage, battery, or electricity, may be supplied to the aircraft 13 via the hanging body 12 and the attachment/detachment part 21.

In addition, in the aircraft takeoff and landing system 10, the suspended body 12 and/or the detachable part 21 are preferably configured to be capable of absorbing the impact when the detachable part 21 collides with the suspended body 12. In this case, too, it is possible to prevent the detachable part 21 from colliding with the suspended body 12 during landing, which would result in damage to the suspended body 12, the detachable part 21, etc. Furthermore, when the detachable part 21 collides with the suspended body 12, it is possible to prevent the aircraft 13 and the suspended body 12 from bouncing back, allowing the aircraft 13 to land more reliably. As a configuration capable of absorbing the impact during collision, it is preferable, for example, to form the suspended body 12 and the detachable part 21 from a flexible material, or to provide a damper in the suspended body 12 and the detachable part 21.

In addition, in the aircraft takeoff and landing system 10, the detachable part 21 may be provided so as to be capable of changing between a protruding state in which it extends upward from the aircraft 13 and a stored state in which it protrudes upward from the aircraft 13 by a smaller amount than in the protruding state. In this case, by putting the detachable part 21 in the protruding state when landing, it is possible to make landing easier. Also, by putting the detachable part 21 in the stored state during flight, it is possible to prevent the detachable part 21 from colliding with or getting caught on something during flight.

Also, as shown in FIG. 11, the aircraft takeoff and landing system 10 may be installed underwater, with the suspended body 12 attached to, for example, the bottom of a floating body 7 floating on the water or a ship moving on the water, an object installed underwater, or an object floating or moving in the water. In this case, it can be used not only for the aircraft 13, but also for the underwater moving body 8, and can be expanded as a takeoff and landing system for them.

As shown in FIG. 12, the aircraft takeoff and landing system 10 may have a long and thin pole 51 with a lower end 51a installed and extending vertically upward, instead of the suspended body 12. In this case, the lower end 51a of the pole 51 is installed on the support base 61 via the damper 52, and the pole 51 is rotatable around the lower end 51a so that the upper end 51b can move in any horizontal direction. The damper 52 is configured to apply a biasing force to the pole 51 when the upper end 51b of the pole 51 moves in any horizontal direction and rotates, thereby returning the pole 51 to a state in which it extends vertically upward. The aircraft 53 has a detachable part 53a that is provided on the lower or side part, rather than on the upper part, and is engageable with the pole 51. In a specific example shown in FIG. 12, the detachable part 53a has a dogleg shape that opens laterally so as to sandwich the pole 51.

In this case, the flying object 53 can land on the pole 51 regardless of the direction from which it approaches the pole 51. When landing, the flying object 53 only needs to be guided so that the detachable part 53a engages with the elongated pole 51. This makes it easier to control the flying object 53 compared to when the flying object 53 is guided almost pinpoint-wise, and the flying object 53 can land smoothly in a relatively short time. Even if the detachable part 53a collides with the pole 51 during landing, the damper 52 can soften the impact of the collision. Therefore, the flying object 53 may be made to collide with the pole 51 while being given momentum, as long as the impact is within the range of impact that can be absorbed by the damper 52. Furthermore, when taking off, the flying object 53 can be moved diagonally upward or to the side to release the detachable part 53a from the pole 51. Therefore, the flying object 53 can take off smoothly and safely in a relatively short time simply by actively moving it.

Reference Signs List 1 Pedestal 2 Column 3 Stand 4 Mobile body 5 Ship 6 Airplane 7 Floating body 8 Underwater mobile body

REFERENCE SIGNS LIST 10 Aircraft take-off and landing system 11 Support part 11a One end part 11b Other end part 12 Suspension body 12a Engagement part 12b Universal joint 13 Aircraft 21 Detachment part 21a Arm 21b Detachment mechanism

31 Arm portion 32 Finger portion 33 Suction cup 34 Curved surface

Claims (9)

A support portion;
A hanging body that is elongated and extends downward with an upper end supported by the support portion, and has an engagement portion at a lower end;
and a flying body having an attachment/detachment part provided at an upper part so as to be engageable with the engagement part of the hanging body,
the flying object is configured to be able to release the detachable part from the engaging part by moving upward or sideways from a state in which the detachable part and the engaging part are engaged with each other ,
The suspension body comprises an elongated pole, the engagement portion being movable in any horizontal direction, and the upper end portion being rotatably attached to the support portion . A support portion;
A hanging body that is elongated and extends downward with an upper end supported by the support portion, and has an engagement portion at a lower end;
and a flying body having an attachment/detachment part provided at an upper part so as to be engageable with the engagement part of the hanging body,
the flying object is configured to be able to release the detachable part from the engaging part by moving upward or sideways from a state in which the detachable part and the engaging part are engaged with each other,
The suspending body and/or the detachable part are provided so as to be capable of absorbing an impact when the detachable part collides with the suspending body.
A takeoff and landing system for an aircraft. 3. The aircraft takeoff and landing system according to claim 1 , wherein the suspended body is disposed with a space at least below and to one side of the engagement portion. The aircraft takeoff and landing system of any one of claims 1 to 3, characterized in that the detachment part is configured to engage with the engagement part by moving toward the engagement part while in contact between the upper end part of the suspended body and the engagement part. An aircraft takeoff and landing system as described in any one of claims 1 to 4, characterized in that the detachment portion is configured to be released from the engagement portion by moving from the engagement portion toward the upper end along the extension direction of the suspended body. An aircraft takeoff and landing system as described in any one of claims 1 to 5 , characterized in that it is configured to be able to supply a predetermined object, substance, or energy to the aircraft via the suspended body and the detachable part. A take-off and landing device for landing an aircraft, comprising:
A support portion;
A hanging body that is elongated and extends downward with an upper end supported by the support portion, and has an engagement portion at a lower end,
The flying object has an attachment/detachment part provided at an upper part thereof so as to be able to engage with the engagement part of the hanging body,
The hanging body comprises a long, thin pole, the engagement portion is movable in any horizontal direction, the upper end portion is rotatably attached to the support portion, and the detachment portion is configured to be released from the engagement portion when the aircraft moves upward or to the side from a state in which the attachment/detachment portion and the engagement portion are engaged. A take-off and landing device for landing an aircraft, comprising:
A support portion;
A hanging body that is elongated and extends downward with an upper end supported by the support portion, and has an engagement portion at a lower end,
The flying object has an attachment/detachment part provided at an upper part thereof so as to be able to engage with the engagement part of the hanging body,
The suspending body is provided so as to be capable of absorbing an impact when the detachable part collides with the suspending body, and is configured so as to be capable of releasing the detachable part from the engaging part when the flying object moves upward or to the side from a state in which the detachable part and the engaging part are engaged with each other.
A takeoff and landing device for an aircraft. A flying object that takes off and lands using a suspended body that is elongated, supported at its upper end and extends downward, and has an engagement portion at its lower end,
The detachable portion is provided at an upper portion thereof so as to be engageable with the engagement portion of the hanging body, and is configured to be capable of being released from the engagement portion by moving the detachable portion upward or to the side from a state in which the detachable portion and the engagement portion are engaged with each other,
The flying object , wherein the detachable part is configured to be capable of absorbing an impact when the detachable part collides with the suspended body .

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