WO2018135383A1 - Buoyant-type flying body - Google Patents

Abstract

The purpose of the present invention is to provide a buoyant-type flying body with which it is possible to inhibit deformation of the outer shape or breakage of a buoyant body. A buoyant-type floating body 1, 100, 100A provided with a buoyant body 2, 110, 110A formed by sealing therein a gas having a specific gravity lower than that of air, wherein: the buoyant body 2, 110, 110A is formed by sealing therein a gas having a specific gravity lower than that of air, or configured so that air therein is expelled to the exterior by thermal energy so as to impart the body with buoyancy; and the buoyant body 2, 110, 110A has an outer skeleton body 21, 120, 120A constituting the outer shape of the buoyant body 2, 110, 110A and exhibiting rigidity.

Description

Levitation aircraft

The present invention relates to a levitation type aircraft including a levitation aircraft body.

2. Description of the Related Art Conventionally, a levitation type flying body including a levitation body formed by sealing a gas having a specific gravity smaller than that of air is known (for example, see Patent Document 1). The external shape of the levitation machine described in Patent Document 1 is made of a resin film that is lightweight and has high strength. There is also known a levitation vehicle equipped with a levitation body configured to give buoyancy to the body by expelling the internal air to the outside with thermal energy and lowering the air density in the body.

Japanese Patent No. 5875093

In the levitation type aircraft described in Patent Document 1, the outer shape of the levitation aircraft is constituted by a resin film, and there is a possibility of crashing if the resin film is damaged. Further, if the outer shape of the levitation aircraft is deformed under the influence of wind, there is a possibility that the high movement ability of the levitation aircraft cannot be exhibited. Therefore, it is desired that breakage of the levitating body and deformation of the outer shape can be suppressed.

Therefore, an object of the present invention is to provide a levitation aircraft that can suppress breakage of the levitation aircraft and deformation of the outer shape.

The present invention is a levitation aircraft including a levitation body, wherein the levitation body is formed by sealing a gas having a specific gravity smaller than that of air inside, or expelling the inside air to the outside by heat energy. The present invention relates to a levitation type flying body that is configured to give buoyancy to an airframe and that has an outer skeleton that forms an outer shape of the levitation body and has rigidity.

In addition, the exoskeleton body is preferably configured to include a planar partition structure that is formed into a planar shape having a predetermined thickness and is partitioned into a plurality of spaces by a plurality of walls.

Further, the planar partition structure has a honeycomb structure having a plurality of hexagonal structures each having a hexagonal cross-sectional shape extending in the thickness direction.

Further, it is preferable that the exoskeleton has a core material that is disposed inside the planar partition structure and supports the planar partition structure.

Further, it is preferable to further include a reinforcing member that reinforces the exoskeleton by protruding from the exoskeleton to the side of the exoskeleton.

Further, it is preferable that the levitation body is formed with an acute outer peripheral edge in a side view.

Further, it is preferable that one or a plurality of the levitation bodies are provided, and a thin portion serving as a horizontal wind passage is formed in at least two directions.

Further, the levitation body is formed by sealing a gas having a specific gravity smaller than air inside, and the levitation body is arranged inside the exoskeleton body so as to partition the interior of the exoskeleton body into a plurality of air chambers. It is preferable to further have a plurality of air sac bodies that are formed by being surrounded by a resin-like film.

Further, it is preferable that the levitation body further includes an outer air sac body that is disposed between the exoskeleton body and the plurality of air sac bodies and is formed in a shape substantially the same as the exoskeleton body by a resin-like film.

According to the present invention, it is possible to provide a levitation aircraft that can suppress breakage of the levitation aircraft and deformation of the outer shape.

It is a top view which shows 1st Embodiment of the floating type flying body which concerns on this invention. It is a side view which shows the floating type flying body of 1st Embodiment. It is a longitudinal cross-sectional view which shows a levitation machine body. It is a cross-sectional view which shows a levitation machine body. It is a figure which shows the process which inject | pours gas into a levitation machine body and gives an internal pressure to a levitation machine body. It is a top view which shows 2nd Embodiment of the floating type flying body which concerns on this invention. It is a side view which shows the inner side support frame of 2nd Embodiment. It is a perspective view which shows the inner side support frame of 2nd Embodiment. It is a cross-sectional perspective view which shows the exoskeleton body of 2nd Embodiment. It is sectional drawing which shows the exoskeleton body of 2nd Embodiment. FIG. 6 is a cross-sectional perspective view showing a modification of the second embodiment and showing a case where the planar partition structure of the exoskeleton is a honeycomb structure. It is a figure which shows 3rd Embodiment of the floating type flying body which concerns on this invention.

(First embodiment)
Hereinafter, a first embodiment of a buoyant aircraft of the present invention will be described with reference to the drawings. The overall configuration of the levitation aircraft 1 according to the present embodiment will be described with reference to FIGS. 1 and 2.

As shown in FIGS. 1 and 2, the levitation type aircraft 1 according to the present embodiment includes a plurality (four) of levitation bodies 2 in which a gas having a specific gravity smaller than air is sealed, and a plurality of vertical propulsion units. Propeller group 3, a plurality of horizontal propeller propeller groups 4, a plurality of floating body support frames 51, a plurality of vertical propeller propeller support frames 52, a plurality of horizontal propeller propeller support frames 53, and a camera 6 .

As shown in FIG. 1, the levitation aircraft 1 is formed in a shape that is symmetrical in the front-rear direction and in the left-right direction in plan view. Further, as shown in FIG. 2, the floating flying vehicle 1 is formed in a vertically and laterally symmetrical shape in a side view except for a camera 6 described later. Each configuration will be described below.

The four levitation machines 2 of the present embodiment are each formed in a flat disk shape with a thin outer peripheral part. The levitation body 2 is formed in a circular shape in plan view. The four levitation bodies 2 are arranged in a horizontal direction in two vertical rows and two horizontal rows in a square range in plan view, and each is formed independently. The four levitation machines 2 are arranged close to or in contact with each other with the flat portions of the levitation machines 2 arranged in the horizontal direction.

The levitation machine body 2 seals a gas having a specific gravity smaller than that of air inside, thereby obtaining buoyancy due to the difference in specific gravity between the surrounding air and the gas, thereby making it easier to float in the air. The inside of the levitation body 2 is filled with a gas having a specific gravity smaller than that of the surrounding air, such as helium, hydrogen, or air heated from the surrounding air, oxygen, and nitrogen. In addition, the shape of the levitation machine body 2 is not limited to a disk shape (circular shape). Moreover, in this embodiment, although the levitation machine body 2 is formed independently, it is not limited to this, Four levitation machine bodies 2 are formed integrally, and it connects and comprises in the flat part of each levitation machine body 2. May be.
The inside of the levitation machine body 2 is partitioned into a plurality of air chambers. Details of the levitation machine body 2 will be described later.

As shown in FIG. 1, a vertical opening 10 is formed between the four levitating bodies 2 at a substantially central position of the levitation-type flying body 1 to allow the vertical air flow. In the present embodiment, a connecting frame 512 of a levitation machine body support frame 51 to be described later is disposed in the vertical direction opening 10, and a plurality of vertical direction opening parts 10 are provided in the linking frame 512 of the levitation machine body support frame 51. Are divided into openings 11.

Further, as shown in FIG. 2, the levitating machine body 2 is formed in a shape in which the center bulges in the vertical direction in a side view, and is inclined toward the outer peripheral edge so that the inclination angle is acute. Is formed. Thereby, the levitation machine body 2 is formed in a flat shape with a thin outer peripheral portion by forming the outer peripheral edge in an acute angle shape.

The wind generated by the horizontal propulsion propeller 41 passes through the thin part of the levitation aircraft 2 as shown by the two-dot chain line arrow shown in FIG. In the present embodiment, a thin portion serving as a wind path in the horizontal direction is formed in two directions. By forming the thin portion that becomes the path of the wind in the horizontal direction in two directions, the lift force of the blades 42 (see FIG. 2) can be efficiently converted into a propulsive force.

As shown in FIGS. 1 and 2, the levitation machine body support frame 51 includes a levitation machine body support frame body 511 and a connection frame 512. The levitation machine body support frame main body 511 is disposed so as to surround the outer surface of each levitation machine body 2. The connection frame 512 is disposed at the approximate center of the floating aircraft 1 in plan view. The connection frame 512 connects the four levitation aircraft body support frame bodies 511 at the approximate center of the levitation aircraft 1 in plan view.

The propeller support frame 52 for vertical propulsion is formed so as to protrude outward from each levitation body 2 at each corner of a square region where the four levitation bodies 2 of the levitation type aircraft 1 are arranged in plan view. The levitation machine body support frame 51 is connected. The propeller support frame 52 for vertical propulsion functions as a frame for attaching the propeller group 3 for vertical propulsion.

In a plan view, the propeller support frame 53 for horizontal propulsion is located outside the side of the levitation aircraft 1 at the center of each side of a square area where the four levitation aircraft bodies 2 of the levitation aircraft 1 are disposed. It is formed so as to protrude and is connected to the levitating machine body support frame 51. The propeller support frame 52 for vertical propulsion functions as a frame for attaching the propeller group 4 for horizontal propulsion.

The levitating body support frame 51, the vertical propeller support frame 52, and the horizontal propeller support frame 53 need only be formed of a lightweight and high-strength material, such as plastic, aluminum, high-rigidity rubber, or urethane. The resin may be coated with carbon fiber reinforced plastic or the like.

The levitation machine body support frame 51, the vertical propeller propeller support frame 52, and the horizontal propeller propeller support frame 53 are configured by, for example, a frame member having a hollow inside.
For example, as shown in FIG. 2, the levitation body support frame main body 511 is opposite to the levitation body 2 in the cross section orthogonal to the direction in which the levitation body support frame main body 511 extends. And an outer portion 55 formed on the side. The inner part 54 is formed in a planar shape and is disposed along the outer surface of the levitation machine body 2. The outer portion 55 is formed in a mountain-valley shape, and includes two peak portions 551 and a valley portion 552 formed between the two peak portions 551. The outer side part 55 is arrange | positioned facing the opposite side to the levitation machine body 2.

The vertical propeller group 3 is for propelling the levitation body 2 in the vertical direction, and includes a plurality of vertical propellers 31. The plurality of vertical propeller propellers 31 are attached to the vertical propeller propeller support frame 52 at each corner of a square region where the four levitating aircraft bodies 2 of the buoyant aircraft 1 are disposed. Each propeller 31 for vertical propulsion is fixed in a state where the rotation axis of the rotary motor 33 is directed in the vertical direction so that the propulsive force is exerted in the vertical direction.

As shown in FIG. 1, each vertical propeller 31 has a set of three blades 32, a rotation motor 33 that rotates these blades 32, and a protective ring 34 provided on the outer periphery of the blades 32. . As the blade 32, a blade used in a general propeller is adopted. The propeller 31 for vertical propulsion can use a relatively small blade 32 because a large lift is not necessary because the levitation body 2 is easily lifted by buoyancy due to a difference in density between gas and air.

The horizontal propeller group 4 is for propelling the levitation body 2 in the horizontal direction, and includes a plurality of horizontal propellers 41. The plurality of horizontal propulsion propellers 41 are attached to the horizontal propulsion propeller support frame 53 at the center of each side of the square area where the four levitating aircraft bodies 2 of the levitation type aircraft 1 are disposed. Each horizontal propeller 41 is fixed in a state where the rotating shaft of the rotary motor 43 is directed toward the center of the levitation body 2 so that the propulsive force is exerted in the horizontal direction.

As shown in FIG. 2, each horizontal propeller 41 has a set of three blades 42, a rotation motor 43 that rotates these blades 42, and a protective ring 44 provided on the outer periphery of the blades 42. . Since the horizontal propeller 41 is mainly used for horizontal movement, relatively small blades 42 can be used.

As shown in FIG. 2, the camera 6 is installed below the vertical opening 10 (see FIG. 1). The camera 6 is an omnidirectional camera for performing aerial shooting. In addition, the installation position of the camera 6 is not limited to the lower part of the up-down direction opening part 10, You may select arbitrarily, such as the upper direction of the levitation machine body 2, an outer periphery. In addition, the levitation aircraft 1 of the present invention is not limited to the camera 6 and may be configured to hold a load or carry a person.

Further, a solar power generation element (not shown) is provided on the surface of the levitation machine body 2 to generate electric power for operating the vertical propeller 31 and the horizontal propeller 41. ing.

Next, the details of the levitation machine body 2 will be described.
As shown in FIGS. 3 and 4, the levitating machine body 2 includes an outer skin body (exoskeleton body) 21 formed by a metal film (metal-like film) constituting the outer shape of the levitating machine body 2, and an inside of the outer skin body 21. A plurality of air sac bodies 22 formed by being disposed and surrounded by a resin film (resin-like film), and an outer air sac body 23 disposed between the outer skin body 21 and the plurality of air sac bodies 22 .

The metal coating of the outer skin 21 has rigidity and constitutes the outer shape of the levitating machine body 2. The metal film is formed in a film shape having a predetermined thickness. Since the metal coating forms the outer shape of the levitation machine body 2, it is formed in a circular shape in plan view and in a shape in which the center bulges in the vertical direction in side view as in the outer shape of the levitation machine body 2. Has been. In addition, the metal film of the outer skin body 21 is inclined toward the outer peripheral edge, and the inclination angle is formed in an acute angle.

The metal coating of the outer skin 21 is preferably made of a coating of a metal material and has strength and weight reduction. The thickness of the metal film is appropriately set in consideration of a portion requiring strength. In the present embodiment, the thickness of the metal film is, for example, about 30 to 150 μm. In the present embodiment, for example, a metal film having a thickness of 30 μm and 1 m × 1 m and having a weight of about 70 g is used.

Examples of the material for the metal film include titanium alloys. In the present embodiment, for example, an alloy obtained by adding lithium and aluminum to magnesium is used as the material of the metal film. When a metal alloy is used as the material for the metal film, the strength and specific gravity can be adjusted by the ratio of each substance.

The production of the metal film is performed, for example, by sticking a film-like metal formed of a predetermined material to an arc-shaped iron kiln and then baking the pasted metal. More specifically, a pair of upper and lower metal films having a central portion bulged so as to correspond to the upper half and the lower half of the outer skin body 21 are created by baking. And the metal film of the outer_body | cover_body 21 can be manufactured by joining the upper part and lower part created by baking by welding etc. FIG. The strength of the metal film can be improved by tempering a film-like metal.

In this embodiment, the exoskeleton is configured by the metal film of the outer skin 21, but the present invention is not limited to this. For example, instead of the metal film of the outer skin body 21 of the present embodiment, the exoskeleton bodies 120 and 120A (see FIGS. 9 and 11) having the planar partition structures 130 and 130A of the second embodiment described later are configured. May be. In this case, like a planar partition structure 130A according to a modification of the second embodiment, the honeycomb structure having a plurality of hexagonal structures 136 (see FIG. 11) having a hexagonal cross section. May be.

The plurality of air sac bodies 22 are arranged inside the outer body 21, as shown in FIGS. The air sac 22 is disposed inside the outer skin 21 so as to partition the inner portion of the outer skin 21 into a plurality of air chambers. In the present embodiment, the plurality of air sac bodies 22 are composed of a central side air sac body 221 and an outer peripheral side air sac body 222.

The inside of the central air bladder body 221 and the outer peripheral air bladder body 222 is filled with a gas having a specific gravity smaller than that of air. A gas having a specific gravity smaller than that of air is hermetically filled between the outer air sac body 23 and the plurality of air sac bodies 22. Thereby, as shown in FIG.3 and FIG.4, several sealed space for filling with gas is formed in the inside of the levitation body 2. As shown in FIG. The gas to be sealed is preferably helium gas or hydrogen gas, but is not limited thereto.

The central air sac body 221 is formed of a resin film, and is formed in a spherical shape as shown in FIGS. As shown in FIG. 4, the central air sac body 221 is disposed at a substantially center inside the outer skin body 21 in a plan view. As shown in FIG. 3, the upper end and the lower end of the central air sac body 221 are in contact with the upper inner surface and the lower inner surface of the outer skin body 21. As shown in FIGS. 3 and 4, the peripheral surface of the side portion of the central air sac body 221 abuts on the inner peripheral surface of the outer peripheral air sac body 222.

The outer peripheral air bladder 222 is formed of a resin film, and is formed in an annular shape as shown in FIG. 4 in a plan view. As shown in FIG. 3, the outer peripheral side air sac body 222 is formed in a flat shape with a thin outer peripheral part by forming the outer peripheral edge with an acute angle. As shown in FIG. 4, the outer peripheral air bladder 222 is disposed along the outer periphery of the side portion of the central air bladder 221 in plan view. The outer peripheral air bladder 222 is disposed between the outer peripheral surface of the central air bladder 221 and the inner surface of the outer skin 21. As shown in FIGS. 3 and 4, the inner peripheral surface of the outer peripheral air bladder 222 abuts on the peripheral surface of the side portion of the central air bladder 221. The outer surface of the acute angle portion on the outer side of the outer peripheral air bladder 222 is in contact with the inner surface of the acute angle portion of the outer edge portion of the outer skin body 21.

The resin film of the center side air sac body 221 and the outer peripheral side air sac body 222 is preferably formed of a resin material film and having strength and weight reduction. In the present embodiment, the strength of the resin film of the central air bag body 221 and the outer air bag body 222 is configured to be lower than the strength of the metal film of the outer skin body 21 described above. In the present embodiment, the thickness of the resin film is, for example, about 25 μm to 35 μm.

The outer air sac body 23 is formed by a resin-like film. The outer air sac 23 is formed in substantially the same shape as the outer skin 21 and is disposed along the inner surface of the outer skin 21.

Examples of the material of the resin film on the air sac body 22 and the outer air sac body 23 include, for example, a resin such as a fiber reinforced plastic using carbon fiber or glass fiber as a lightweight and high strength material. Specifically, examples of the material for the resin film include a high barrier film, polyethylene, polyarylate fiber, and polyester fiber. Note that the resin film is not limited to this, and may be formed of other materials according to cost and the like.

Next, the procedure for manufacturing the levitation machine body 2 will be described. In the present embodiment, a procedure for filling a gas having a specific gravity smaller than that of air into the plurality of air sac bodies 22 (center side air sac body 221, outer peripheral side air sac body 222) and outer skin body 21 will be described.

First, before filling the inside of the outer skin body 21 and the plurality of air sac bodies 22 in the levitation body 2 with a gas having a specific gravity smaller than air, the outer air sac body along the inner surface of the outer skin body 21 as shown in FIG. 23, a central air sac body 221 is disposed in the center of the outer air sac body 23 (outer skin body 21), and the outer side of the central air sac body 221 inside the outer air sac body 23 (outer body 21). The outer peripheral air sac body 222 is disposed.

As shown in FIG. 5, the outer air sac body 23 is formed in substantially the same shape as the outer skin body 21, and is disposed between the outer skin body 21 and the plurality of air sac bodies 22 along the inner surface of the outer skin body 21.
Before the center side air sac body 221 is filled with a gas having a specific gravity smaller than that of air, the center in the horizontal direction swells in the vertical direction and the outer peripheral edge is formed in a flat shape as shown in FIG.
As shown in FIG. 5, the outer peripheral air bladder 222 is formed in an annular shape as a whole, and has a cross-sectional shape of an isosceles triangle having a vertex at the outer peripheral edge before filling with a gas having a specific gravity smaller than that of air. Formed. By forming the cross-sectional shape of the outer air bladder 222 in the shape of an isosceles triangle, the acute angle shape of the outer peripheral edge of the levitation machine body 2 can be suitably supported from the inside by the apex portion of the isosceles triangle shape.

After the outer air sac body 23, the central air sac body 221 and the outer peripheral air sac body 222 are arranged inside the outer skin 21, the central air sac body 221 and the outer air sac body 222 inside the outer air sac body 23 are arranged. Considering that the central air sac body 221 and the outer peripheral side air sac body 222 filled with gas inside the outer air sac body 23 are arranged in a portion that is not present, a small amount of gas having a specific gravity smaller than that of air is filled. Then, a gas having a specific gravity smaller than that of air is filled in the outer side air sac body 222 about 85% when the full filling is 100%. Then, a gas having a specific gravity smaller than that of air is filled in the central air sac body 221 to about 100% when full filling is assumed to be 100%.

Thereby, as shown in FIG. 5, the pressure inside the outer skin 21 becomes equal to the external pressure. Therefore, the pressure is applied to the outer skin body 21 evenly in any part.

Here, since the outer shape of the outer skin body 21 is formed of a metal film, the outer skin body 21 does not swell before and after the central air bladder body 221 and the outer circumferential air bladder body 222 are filled with a gas having a specific gravity smaller than that of air. The shape of the outer skin 21 can be formed in a preset shape.

Further, by arranging a plurality of air sac bodies 22 inside the outer skin body 21, it is easy to maintain the acute-angled shape of the outer peripheral edge of the levitation machine body 2. More specifically, there is little effect when the levitation aircraft 1 moves in a slow motion, but when the levitation aircraft 1 moves at a higher speed, the shape of the levitation aircraft body 2 is stable due to air resistance. It is important to move in. In particular, when the shape of the outer skin body 21 is deformed or the film of the outer skin body 21 vibrates, the stability of the levitation machine body 2 is significantly reduced. However, the outer skin body 21 filled with gas has a characteristic of naturally rounding even if it is not made of rubber and is a metal film, and a portion that is difficult to round tends to be rounded and rounded. Therefore, when the space inside the outer skin 21 is filled with gas at once, it is difficult to form the outer peripheral edge of the outer skin 21 with an acute angle.

Here, in order to make the outer peripheral edge of the levitation body 2 have an acute angle shape, at least two or more of a central central air sac body 221 and an outer peripheral air sac body 222 on the outer peripheral side are provided inside the outer skin body 21. An air chamber is required. When the pressure of the central air sac body 221 increases, the pressure is equally applied to 360 degrees around the central air sac body 221. However, due to the restriction of the expansion of the central air sac body 221 in the center of the outer skin 21 to the upper and lower sides, the outer peripheral air sac body 222 on the outer peripheral side with a small amount of gas and low pressure is pressurized by the central air sac body 221. The Therefore, by applying sufficient pressure to the outer peripheral edge of the levitating machine body 2, the levitating machine body 2 can be brought closer to a flat sphere whose outer peripheral edge is formed in an acute angle shape more rationally than in the case of one air chamber. . Further, the outer skin body 21 is formed of a metal film, and pressure is applied to the central air sac body 221 at the center so that the outer peripheral edge of the outer peripheral air sac body 222 is corrected to be flat, thereby making a single metal film. A rational flat sphere can be formed reasonably with a thin metal film, rather than forming one air chamber with the outer skin body 21 configured as described above and correcting the gas layer to be flat.

In the present embodiment, the inside of the levitation machine body 2 is divided into a plurality of air chambers, and the inside of the outer peripheral air sac body 222 forming an acute-angled portion of the outer peripheral edge of the levitation machine body 2 is filled with about 85% of gas. After that, the levitation machine body 2 is formed by filling about 100% of the gas into the inside of the central air sac body 221 disposed inside the outer air sac body 222. Therefore, the shape of the levitation machine body 2 can be formed close to a preset shape. Further, by forming the interior of the levitation body 2 into a plurality of air chambers, it is possible to reduce the tendency of the whole to become round when the levitation aircraft 1 moves, and the acute angle of the outer peripheral edge of the levitation body 2. The deformation of the shaped part can be reduced.

In the above levitation body 2, since the outer peripheral edge of the levitation body 2 is formed in an acute angle shape, the wind pressure from the side surface of the levitation body 2 is received during the horizontal flight of the levitation aircraft 1. As shown, the wind pressure is divided in the vertical direction and flows along the upper and lower surfaces of the levitation machine body 2. Therefore, resistance due to wind pressure is suppressed, and the flight speed is improved. Furthermore, in this embodiment, since the sharp outer shape of the outer peripheral edge of the levitation machine body 2 is formed by the metal film of the outer skin body 21, the acute angle shape of the outer peripheral edge of the levitation machine body 2 is not easily deformed, and is long. Allows continuous flight of time. In addition, as described above, the interior of the levitation machine body 2 is divided into a plurality of air chambers, and the outer skin body 21 formed of a metal film is formed with a portion where pressure is increased and a portion where pressure is decreased. When the levitation aircraft 1 moves, the deformation of the acute angle portion of the outer peripheral edge of the levitation aircraft body 2 can be reduced.

According to the floating aircraft 1 of the present embodiment as described above, the following effects can be obtained.

(1) The levitation aircraft 1 includes a levitation body 2 formed by sealing a gas having a specific gravity smaller than that of air, and the levitation body 2 forms the outer shape of the levitation body 2 and is rigid. And a plurality of air sac bodies formed by being disposed inside the outer skin body 21 and surrounded by a resin film so as to partition the inside of the outer skin body 21 into a plurality of air chambers. 22 and so on.
Thus, by forming the outer shape of the levitating body 2 with a metal film, the outer shape can be formed into a preset shape and having a strength rather than being formed with a resin film. Can be formed into a design. Therefore, the levitating body 2 can reduce the deflection due to the wind pressure when moving at a high speed, and can stabilize the flight of the levitating aircraft 1.
In addition, since the outer skin body 21 has rigidity, the outer skin body 21 can be prevented from being damaged even when attacked by insects or birds.
Moreover, since the external shape of the levitating machine body 2 is formed with the metal film of the outer skin body 21, the external shape of the levitating machine body 2 is hard to deform | transform, and air resistance can be reduced rather than an external shape being formed with a resin film. Therefore, the flight control of the levitation aircraft 1 is easy to be stabilized, and a long continuous flight is possible.
A central air sac body 221 and an outer peripheral air sac body 222 are arranged inside the outer skin 21. Therefore, the outer skin body 21 is supported by being pressurized by a plurality of air sac bodies 22 from the inside. Thereby, even if the thickness of the metal film that forms the outer skin body 21 is reduced, the strength of the levitation machine body 2 can be maintained. Even if any one of the outer skin 21, the central air sac body 221, or the outer peripheral air sac body 222 is damaged due to external pressure or the like, the inner part of the outer skin 21 is divided into a plurality of air chambers. Even if the portion is damaged, the entire buoyancy of the levitation type aircraft 1 is not lost. Thereby, the rapid descent of the levitation type flying vehicle 1 can be suppressed.
Moreover, the outer skin body 21 is formed of a metal film, and the outer shape of the levitation machine body 2 can be formed into a preset shape and is not easily deformed. Therefore, even when the air sac body 22 surrounded by the resin film is about to expand when the levitation machine body 2 is raised, the outer skin body 21 formed of the metal film is disposed outside the air sac body 22, and the levitation body 2 is , The expansion is suppressed. Thereby, it can suppress that the buoyancy of the levitation machine body 2 becomes large too much, and can suppress that the levitation machine body 2 raises too much. Therefore, the buoyancy of the levitation aircraft 1 can be stabilized.

(2) The levitation machine body 2 has an outer peripheral edge formed in an acute angle shape in a side view. Therefore, since the levitation body 2 is formed in a shape that can reduce the air resistance, the flight control of the levitation aircraft 1 can be easily performed, the flight speed can be improved, and continuous flight for a long time is possible. And

(3) The levitation type aircraft 1 is formed with at least two thin portions that serve as wind paths in the horizontal direction. Therefore, since the wind passes through the thin part of the levitation aircraft 1 in the horizontal direction, the lift can be efficiently converted into propulsion in the levitation aircraft 1.
For example, the horizontal movement of the levitation aircraft 1 is performed mainly by operating the horizontal propeller group 4. The propeller group 4 for horizontal propulsion exerts a thrust in the horizontal direction by rotating the blades 42 with a rotary motor 43. At this time, the wind generated by the propeller 41 for horizontal propulsion passes through a thin portion of the floating aircraft 1 as shown in FIG. 1, so that the lift force of the blades 42 can be efficiently converted into a propulsion force. .

(4) The levitation machine body 2 is configured to include an outer air sac body 23 which is disposed between the outer skin body 21 and the plurality of air sac bodies 22 and is formed by a resin-like film having substantially the same shape as the outer skin body 21. Thereby, since the outer air sac body 23 holds the plurality of air sac bodies 22 from the outside, the levitation body 2 can be formed in a stable shape, and the shape of the levitation body 2 can be maintained during the flight of the buoyant aircraft 1. .

(Second Embodiment)
Hereinafter, a floating aircraft 100 according to a second embodiment of the present invention will be described with reference to the drawings. The overall configuration of the levitation aircraft 100 according to the second embodiment will be described with reference to FIGS.

As shown in FIG. 6, the levitated flying vehicle 100 of the present embodiment is formed in a shape that is symmetrical in the front-rear and left-right directions in plan view. The levitation-type flying body 100 includes one levitation body 110 in which a gas having a specific gravity smaller than that of air is sealed, and a vertical center of the levitation body 110 that is substantially horizontally laterally from an end in the front-rear direction. A pair of outwardly extending reinforcing members (reinforcing members) 160, a plurality of vertical propeller group 3A, and a plurality of horizontal propeller group 4A are provided.

The levitation machine body 110 of the present embodiment is formed to extend in the left-right direction in a plan view, is formed in a shape in which the center in the longitudinal direction bulges in the front-rear direction, and the width decreases toward the outside in the left-right direction. It is inclined so as to be connected by an end 122 extending in the front-rear direction at the end in the longitudinal direction.

The levitation machine body 110, like the levitation machine body 2 of the first embodiment, encloses a gas having a specific gravity smaller than that of air inside to obtain buoyancy due to the specific gravity difference between the surrounding air and the gas, and floats in the air. It is easy to do. As shown in FIG. 6, the levitation machine body 110 includes an exoskeleton body 120 that forms the outer shape of the levitation machine body 110, an inner support frame 170 that is disposed inside the exoskeleton body 120, and an inner support frame 170. A plurality of air sac bodies (not shown).

Also in the second embodiment, a plurality of air sac bodies (not shown) are arranged inside the exoskeleton body 120 as in the first embodiment. The air bag body is filled with a gas having a specific gravity smaller than that of air, as in the first embodiment. The plurality of air sac bodies according to the second embodiment have the same configuration as the air sac body according to the first embodiment. The number and shape of the plurality of air sac bodies are appropriately set depending on the shape of the exoskeleton 120 and the like.

The inner support frame 170 is configured by combining a plurality of frames with a space inside. As shown in FIG. 6, the inner support frame 170 is formed in a shape in which the center in the left-right direction (longitudinal direction) bulges in the front-rear direction in a plan view, and is inclined toward the outer peripheral edge. The inclination angle is formed into an acute angle. Further, as shown in FIG. 7, the inner support frame 170 is formed in a shape in which the center in the left-right direction (longitudinal direction) bulges up and down in a side view, and is inclined toward the outer peripheral edge. The inclination angle is formed into an acute angle.

As shown in FIGS. 7 and 8, the inner support frame 170 includes a plurality of arc-shaped outer edge constituting arc frames 171 and a plurality of vertical frames arranged around the right and left directions at predetermined positions in the left and right directions. The rotating frame 172 and a plurality of horizontal rotating frames 173 arranged to rotate in the left-right direction at a predetermined position in the front-rear direction. The outer edge constituting arc frame 171, the longitudinal circulation frame 172, and the transverse circulation frame 173 are only required to be formed of a lightweight and high-strength material. For example, a resin such as plastic, aluminum, rigid rubber, or urethane is used as a carbon fiber. It may be coated with reinforced plastic or the like.

The four outer edge constituting arc frames 171 constitute the outer edge of the inner support frame 170. The four outer edge-constituting arc frames 171 are formed in an arc shape that bulges outward, and both end portions are connected to each other and are spaced apart from each other by 90 ° in the circumferential direction. The inner support frame 170 is framed by four outer edge constituting arc frames 171, a plurality of longitudinal circulation frames 172, and a plurality of transverse circulation frames 173 with a space inside.

The exoskeleton 120 is attached to the outside of the inner support frame 170 as shown in FIG. As shown in FIGS. 9 and 10, the exoskeleton 120 includes a planar planar partition structure 130 having a predetermined thickness, and a core member 140 disposed inside the planar partition structure 130. A reinforcing skin material 150 disposed on the outer surface of the planar partition structure 130. The planar partition structure 130 and the reinforcing skin material 150 constitute the outer shape of the levitation machine body 110.

The planar partition structure 130 is attached to the outside of the inner support frame 170 (see FIGS. 6 to 8). The planar partition structure 130 is formed in a planar shape having a predetermined thickness, and is configured by a partition structure in which the interior is partitioned into a plurality of spaces by a plurality of walls. Since the planar partition structure 130 is attached to the outside of the inner support frame 170, it is formed in a shape in which the center in the longitudinal direction bulges in the front-rear direction in plan view, like the outer shape of the inner support frame 170, and In the side view, the center in the longitudinal direction is formed in a shape bulging up and down.

As shown in FIGS. 9 and 10, the planar partition structure 130 includes an outer surface wall 131 disposed on the outer side and an inner surface wall 132 disposed on the inner side in the cross-sectional structure. A space between the inner wall 132 and the inner wall 132 is defined.

In the present embodiment, the planar partition structure 130 has an intermediate wall 133 disposed between the outer wall 131 and the inner wall 132 in parallel with the outer wall 131 and the inner wall 132. A two-layer structure is formed between the inner wall 132 and the intermediate wall 133 so as to overlap in the thickness direction.

In each of the two layers overlapping in the thickness direction, the planar partition structure 130 includes a thickness direction extending wall 134 formed at predetermined intervals and extending in the thickness direction, and a thickness direction extending wall 134 in a cross-sectional view. And a semicircular arc wall 135 having a radius. A plurality of arc walls 135 are arranged side by side in a direction orthogonal to the thickness direction in two layers overlapping in the thickness direction. The arc wall 135 is formed in a semicircular arc shape having the thickness direction extending wall 134 as a radius and the intermediate wall 133 side being convex in a state where the thickness direction extending wall 134 is arranged in the radius portion. The two arc walls 135 formed in each of the two layers of the planar partition structure 130 and arranged in the thickness direction are arranged such that the apexes of the arc portions are in contact with the intermediate wall 133 and face each other.

The intermediate wall 133, the thickness direction extending wall 134, and the arc wall 135 are formed between the outer wall 131 and the inner wall 132, and extend in a direction orthogonal to the direction in which the arc walls 135 are arranged. Examples of the material of the planar partition structure 130 (the outer wall 131, the inner wall 132, the intermediate wall 133, the thickness extending wall 134, and the arc wall 135) include a resin material, a metal material, and a carbon nanohorn (carbon). Lightweight and high strength (rigidity) material such as nanohorn (CNH) is used.

The core member 140 is disposed inside the planar partition structure 130 and supports the planar partition structure 130 inside the planar partition structure 130, thereby reinforcing the strength of the planar partition structure 130. The core member 140 is disposed along the intermediate wall 133 between the outer wall 131 and the inner wall 132 inside the planar partition structure 130. In the present embodiment, the core member 140 is connected to the intermediate wall 133 in a state of being embedded in the intermediate wall 133, and one semicircular portion of the core member 140 is outside (on the outer surface wall 131 side) with respect to the intermediate wall 133. The other semicircular portion of the core member 140 is disposed on the inner side (inner wall 132 side) with respect to the intermediate wall 133.

In the present embodiment, the core member 140 includes a pipe-shaped member 141 formed in a long pipe shape and a long reinforcing fiber material 142 disposed inside the pipe-shaped member 141. In the present embodiment, the pipe-shaped member 141 is made of, for example, carbon nanotube (CNT), and the reinforcing fiber material 142 is made of, for example, an aramid fiber (reinforcing fiber material) that is a highly rigid fiber material. Is done.

The reinforcing skin material 150 is formed in a sheet shape, and is disposed on the outer surface of the planar partition structure 130 so as to cover the outer surface of the planar partition structure 130. The reinforcing skin material 150 is attached to the surface of the planar partition structure 130 so as to reinforce the surface of the exoskeleton 120. As the reinforcing skin material 150, for example, a lightweight and high strength material such as carbon nanohorn (CNH) is used. The reinforcing skin material 150 is made of, for example, a coating material of 1 mm or less.

As shown in FIG. 6, the outwardly extending reinforcing member 160 is formed so as to protrude outward from the arcuate edge 121 at the center in the vertical direction of the exoskeleton 120 to the side of the exoskeleton 120. 120 is reinforced. The outwardly extending reinforcing member 160 extends along the arc edge 121 of the exoskeleton 120 and protrudes substantially horizontally from the arc edge 121 outward to the side. The arc edge 121 of the exoskeleton 120 is formed with an acute angle.

The outwardly extending reinforcing member 160 is recessed in the exoskeleton body 120 side in the center in the left-right direction, and four projecting arc portions 161 that project in an arc shape on the outer side of the exoskeleton body 120 are formed on both ends in the left-right direction. Is done. The four projecting arc portions 161 are provided with a pair of left and right projecting arc portions 161 projecting in a curved shape on the outside of the exoskeleton 120 so as to be separated in the front-rear direction.

As shown in FIG. 6, a vertical propeller group 3A is attached to the outwardly extending reinforcing member 160. The propeller group 3A for vertical propulsion is for propelling the levitating body 110 in the vertical direction. Plural (eight) propellers 31A for vertical propulsion are arranged on the outwardly extending reinforcing member 160. The eight vertical propellers 31A are each provided with two vertical propellers 31A on the four projecting arc portions 161 of the outwardly extending reinforcing member 160. Each vertical propeller 31A has the same configuration as the vertical propeller 31 of the first embodiment.

Horizontal propeller groups 4A are arranged at both ends in the left-right direction of the floating aircraft 100. As shown in FIG. 6, the horizontal propeller group 4A is for propelling the levitating body 110 in the horizontal direction, and includes a pair of horizontal propellers 41A on the left and right. Each horizontal propeller 41A has the same configuration as the horizontal propeller 41 of the first embodiment.

The levitation vehicle 100 configured as described above is configured to have rigidity by the exoskeleton 120. Conventionally, in a flying body, water called ballast water is stored in a ballast tank provided inside the flying body, and the flying body is balanced while moving the ballast water by tilting the flying body. However, the flying object was raised or lowered. On the other hand, according to the present invention, the levitation aircraft 100 is configured to have rigidity by the exoskeleton 120. Therefore, the levitation-type aircraft 100 has the propeller group 3A for vertical propulsion and the propulsion group 3A for vertical propulsion in a state in which the outwardly extending reinforcing member 160 maintains the outer shape due to the rigidity of the exoskeleton 120 by strengthening the rigidity of the exoskeleton 120. By driving the horizontal propeller group 4A, it can move freely up, down, left and right without using ballast water.

According to the floating aircraft 100 of the second embodiment as described above, the following effects can be obtained.
(5) The levitation type aircraft 100 is provided with a levitation body 110 formed by sealing a gas having a specific gravity smaller than that of air, and the levitation body 110 constitutes the outer shape of the levitation body 110 and has a rigidity outside. Skeletal body 120 and a plurality of air sac bodies (not shown) formed by being placed inside exoskeleton body 120 and surrounded by a resin-like film so as to partition the inside of exoskeleton body 120 into a plurality of air chambers And including. Thereby, the same effect as (1) of a 1st embodiment can be produced. More specifically, the same effect as that exhibited by the “outer body 21” of the first embodiment can be achieved by the “exoskeleton 120” of the second embodiment.

(6) The exoskeleton 120 is configured to include a planar partition structure 130 that is formed in a planar shape having a predetermined thickness and is partitioned into a plurality of spaces by a plurality of walls. Thereby, the exoskeleton 120 can be further reduced in weight, and the rigidity of the exoskeleton 120 can be further improved.

(7) The exoskeleton 120 is configured to have a core material 140 disposed inside the planar partition structure 130 and supporting the planar partition structure 130. Thereby, since the planar partition structure 130 is supported from the inner side by the core member 140, the rigidity of the exoskeleton 120 can be further improved.

(8) An outwardly extending reinforcing member 160 that protrudes from the exoskeleton body 120 to the side of the exoskeleton body 120 and reinforces the exoskeleton body 120 is further provided. Thereby, since the exoskeleton 120 can be reinforced from the side, the rigidity of the exoskeleton 120 can be further improved.

(Modification of the second embodiment)
A modification of the second embodiment will be described. In the modification of the second embodiment, a description will be given of a case where the planar partition structure 130A of the exoskeleton 120A is configured with a honeycomb structure instead of the planar partition structure 130 of the exoskeleton 120 of the second embodiment. To do. In the following description, components that are the same as or similar to those in the above-described embodiment may be denoted by the same reference numerals and description thereof may be omitted.

As shown in FIG. 11, a planar partition structure 130 </ b> A according to a modification of the second embodiment includes an outer surface wall 131, an inner surface wall 132, and a plurality of hexagonal structures 136 that are sectioned in a hexagonal shape. And a honeycomb structure. The plurality of hexagonal structures 136 are each formed in a cylindrical shape having a hexagonal cross section between the outer wall 131 and the inner wall 132 and extending in the thickness direction. As the material of the planar partition structure 130A (the outer surface wall 131, the inner wall 132, and the plurality of hexagonal structures 136), for example, a resin material or a material similar to the material of the planar partition structure 130 of the second embodiment can be used. In addition, a light material with high strength (rigidity) such as a metal material or carbon nanohorn (CNH) is used.

The above-described planar partition structure 130A has a honeycomb structure, so that it is light and rigid, and can be strengthened. In the present embodiment, since the thickness and the curvature of the surface can be easily set in the honeycomb structure, the planar partition structure 130A can be easily formed. Thereby, a fine curved surface shape can be easily formed in the honeycomb structure.

Further, by forming the planar partition structure 130A with a honeycomb structure, it can be processed with a fine curved surface shape while being a rigid exoskeleton structure of a rigid honeycomb structure. This makes it possible to design a sports-type floating flying object 100 that can reduce wind pressure resistance capable of high-speed flight and is surrounded by a curved surface having a center in the longitudinal direction bulged in the front-rear direction and the vertical direction. Further, by forming the arc edge 121 of the exoskeleton 120 at an acute angle so as to cut the wind, the angle of entry into the wind pressure can be made shallow and the wind pressure resistance can be reduced.

Also, the core material 140 is disposed inside the planar partition structure 130A, as in the second embodiment. The core member 140 reinforces the strength of the planar partition structure 130A by supporting the planar partition structure 130A inside the planar partition structure 130A. Since the configuration of the core member 140 is the same as that of the second embodiment described above, the description thereof is omitted.

(9) In the modification of the second embodiment, the planar partition structure 130A of the exoskeleton 120A is configured with a honeycomb structure. Thereby, the exoskeleton 120A can be further reduced in weight, and the rigidity of the exoskeleton 120 can be further improved. Further, since the thickness and the curvature of the surface can be easily set in the honeycomb structure, the planar partition structure 130A of the exoskeleton 120A can be easily formed.

(Third embodiment)
Hereinafter, a floating flying object 100A according to a third embodiment of the present invention will be described with reference to FIG. Whereas the levitated aircraft 100 of the second embodiment is a hermetic type of aircraft with gas sealed therein, the levitated aircraft 100A of the third embodiment is a balloon type aircraft. In the second embodiment and the third embodiment, the exoskeletons 120 and 120A have the same configuration. In the following description, components that are the same as or similar to those in the above-described embodiment may be denoted by the same reference numerals and description thereof may be omitted.

As shown in FIG. 12, the levitation type aircraft 100A according to the present embodiment includes a single levitation aircraft 110A and a pair of horizontally extending laterally from the front and rear end portions in the vertical center portion of the levitation aircraft 110A. An outwardly extending reinforcing member (reinforcing member) 160, a plurality of vertical propeller group 3A, a plurality of horizontal propeller group 4A, a heat source device 13, a battery 14, a GPS sensor 15, and a monitoring camera A device 16, a transmission unit 17, a plurality of distance measurement cameras 18, and a control unit 12 are provided.

The floating body 110A is formed so as to extend in the left-right direction in a plan view, is formed in a shape in which the center in the longitudinal direction bulges in the front-rear direction and the up-down direction, and becomes narrower toward the outside in the left-right direction. So as to be inclined.

Unlike the levitating machine body 2 of the first embodiment and the levitating machine body 110 of the second embodiment, the levitating machine body 110A is constituted by a balloon type machine body, and the internal air is passed through an opening 111 formed in the upper part. It is configured to give buoyancy to the aircraft by expelling it to the outside with thermal energy and lowering the air density in the aircraft. The heat source device 13 generates heat energy that drives the air inside the levitation machine body 110 </ b> A to the outside.

As shown in FIG. 12, the levitation body 110A includes an exoskeleton body 120A that forms the outer shape of the levitation body 110A, and an inner support frame 170 (see FIG. 12) that is disposed inside the exoskeleton body 120A. 12 (not shown, see FIGS. 7 and 8). Since the exoskeleton 120A has the same configuration as that of the exoskeleton 120 of the second embodiment except that the opening 111 is provided in the upper part, the description thereof is omitted. Moreover, since the inner side support frame 170 (refer FIG.7 and FIG.8) is the structure similar to 2nd Embodiment, description is abbreviate | omitted.

The heat source device 13 is a device that continuously generates a certain amount of heat energy using a predetermined heat energy generating gas (for example, hydrogen gas) inside the levitation body 110A. The heat energy generated by the heat source device 13 expels the air inside the levitation machine body 110A to the outside and gives buoyancy to the levitation machine body 110A. Further, the heat energy generated by the heat source device 13 is converted into electric energy and stored in the battery 14.

The battery 14 stores electric energy converted from the heat energy generated by the heat source device 13 and supplies the stored electric energy to various devices. The battery 14 is electrically connected to the GPS sensor 15, the monitoring camera device 16, the transmission unit 17, the plurality of distance measurement cameras 18, and the control unit 12. The electric energy stored in the battery 14 becomes power for driving the plurality of vertical propeller group 3A and the plurality of horizontal propeller group 4A in the floating aircraft 100A, and the GPS sensor 15, the monitoring camera device 16, A power source for various devices such as the transmission unit 17, the plurality of distance measurement cameras 18, and the control unit 12.

The GPS sensor 15 is a position sensor that detects position information of a current position in GPS (Global Positioning System).
The monitoring camera device 16 captures an image of the lower part of the levitation aircraft 100A during the flight of the levitation aircraft 100A. The monitoring camera device 16 includes a main camera 16a and a spare camera 16b. The main camera 16a is used during normal times, and the spare camera 16b is used in an emergency such as when the main camera 16a breaks down.
The transmission unit 17 transmits an image or video captured by the monitoring camera device 16 to the control unit 12.

The plurality of distance measurement cameras 18 can acquire the surrounding shooting information necessary for performing position control using artificial intelligence (AI) of the control unit 12 to be described later. It is attached to the appropriate part. The plurality of distance measurement cameras 18 acquire imaging information around the floating flying object 100 </ b> A during flight, and transmit the acquired imaging information to the control unit 12.

A GPS sensor 15, a monitoring camera device 16, a transmission unit 17, a plurality of distance measurement cameras 18, a plurality of vertical propeller group 3A and a plurality of horizontal propeller group 4A are electrically connected to the control unit 12. Has been.

The control unit 12 performs position control using artificial intelligence (AI) based on surrounding shooting information shot by a plurality of distance measuring cameras 18. The control unit 12 controls the driving of the plurality of vertical propeller group 3A and the plurality of horizontal propeller group 4A based on the flight path analyzed by the position control using artificial intelligence (AI), so that the floating type The operation of the flying object 100A is controlled.

The control unit 12 grasps the position of the floating flying object 100 </ b> A based on the position information acquired by the GPS sensor 15. In the present embodiment, during normal times, the control unit 12 controls the operation of the levitation aircraft 100A based on the flight path analyzed by position control using artificial intelligence (AI). On the other hand, in the event of an emergency or abnormality, the control unit 12 acquires position information from the GPS sensor 15 in order to grasp the position of the levitation aircraft 100A and collect the levitation aircraft 100A. Control is performed so as to transmit position information to a base station or the like.

In the present embodiment, the levitated aircraft 100A basically flies by position control using artificial intelligence (AI). The GPS sensor 15 is used to collect the levitation aircraft 100A when the location of the levitation aircraft 100A is unknown. When flying centering on position control by the GPS sensor 15, there is a risk of takeover of the levitation aircraft 100 </ b> A. Therefore, in this embodiment, the levitation aircraft 100 </ b> A basically does not use the GPS sensor 15. To fly.

The control unit 12 receives the image information and video information captured by the monitoring camera device 16 and transmitted by the transmission unit 17, and controls image analysis of the captured image captured by the monitoring camera device 16.

The balloon type levitation aircraft 100A of the third embodiment as described above also has the same effects as the above (5) to (9), like the sealed type levitation aircraft 100 of the second embodiment. Obtainable.

Note that the levitation vehicle 1 according to the present invention is not limited to the embodiment described above, and can be changed as appropriate. For example, in the above-described embodiment, the outer shape of the levitation machine body 2 is configured by the outer skin body 21 formed of a metal film, the air sac body 22 is formed by being surrounded by a resin film, and the outer air sac body 23 is formed by a resin film. However, it is not limited to this. Instead of a metal film, a metal-like film composed of a material that is not a metal but has a property similar to a metal may be used.Although it is not a resin, it has a property similar to a resin instead of a resin film. You may use the resin-like film | membrane comprised with the material which has.

In the first embodiment, the outer air sac body 23 is provided. However, the present invention is not limited to this, and the outer air sac body 23 may not be provided.

In the first embodiment, the two resin films are disposed inside the metal film, but the present invention is not limited to this. For example, three or more resin films may be disposed inside the metal film.

In the first embodiment, four levitation machines 2 are provided, but the present invention is not limited to this. One levitation machine body may be provided, and two, three, five or more may be provided.

In the first embodiment, the camera is mounted. However, the present invention is not limited to this. For example, it may be configured such that a person can be boarded or a pesticide for spraying a pesticide may be mounted.

In the second embodiment, the inner support frame 170 is disposed inside the exoskeleton 120. However, the present invention is not limited to this. The inner support frame 170 may not be disposed inside the exoskeleton 120. Further, although the reinforcing outer skin material 150 is disposed on the outer surface of the exoskeleton body 120, the present invention is not limited to this, and the outer skeleton body 120 is not provided with the reinforcing outer skin material 150 on the outer surface of the exoskeleton body 120. You may comprise only the structure 130. FIG.

Further, in the second embodiment, the planar partition structures 130 and 130A are configured by a honeycomb structure having a plurality of hexagonal structures each having a hexagonal cross-sectional shape extending in the thickness direction. It is not limited to. For example, the cross-sectional shape of the planar partition structure may be constituted by other polygons or may be constituted by a circle. Further, the planar partition structure may be constituted by a single polygon or a combination of a plurality of polygons.

Moreover, in the said 1st Embodiment, although the exoskeleton body was comprised with the skin body 21, it is not limited to this, It replaces with the skin body 21 of the said 1st Embodiment, and the planar division structure of 2nd Embodiment. You may comprise with the exoskeleton 120,120A which has 130,130A. In this case, as in a planar partition structure 130A according to a modification of the second embodiment, the honeycomb structure may have a plurality of hexagonal structures 136 that are sectioned in a hexagonal shape.

In the third embodiment, the control unit 12 is configured to control, for example, position control using artificial intelligence (AI) and image analysis of the monitoring camera device 16. Also in the first embodiment and the second embodiment, as in the third embodiment, the control unit 12 controls the position control using, for example, artificial intelligence (AI) and the image analysis of the monitoring camera device 16. And so on.

Further, the levitation aircraft 1 of the first embodiment is a gas-filled aircraft in which the inside of the levitation aircraft 2 is filled with a gas having a specific gravity smaller than air, such as helium gas. Further, the floating flying object 100A of the third embodiment is a hot air balloon type flying object. However, the present invention is not limited to this. You may comprise the hybrid type flight body which used both the gas filling type flight body and the hot air balloon type flight body. For example, in order from the upper side to the lower side, a hot air balloon type flying object and a gas filling type flying object are arranged, and an occupant and a luggage are arranged below the gas filling type flying object. When a hybrid type flying body is configured, the state of gas such as helium gas (activity, etc.) can be controlled even in a place where the outside air temperature is low by using the thermal energy of the hot air balloon type flying body. Specifically, when the outside air temperature is low, the volume of the gas decreases and the volume of the air sac decreases, but the thermal energy of the hot air balloon type aircraft can be used even in a low temperature region such as the polar region. Because it can use maximum buoyancy, it can fly stably even when the outside air temperature changes. Also, by placing a gas-filled aircraft such as helium gas between the hot-air balloon type aircraft and the occupant or baggage, the occupant or baggage is generated from the hot-air balloon type by the gas-filled aircraft. Is shielded from the heat generated.

1,100,100A Levitation Type Aircraft 2,110,110A Levitation Aircraft 21 Outer Body (Exoskeleton Body)
22 Air sac body 23 Outer air sac body 120, 120A Exoskeleton body 130, 130A Planar partition structure 140 Core material 160 Outward extending reinforcing member (reinforcing member)

Claims (9)

1. A levitation aircraft with a levitation aircraft,
   The levitation body is formed by sealing a gas having a specific gravity smaller than that of air inside, or configured to expel the inside air to the outside with thermal energy to give buoyancy to the body. A buoyant flying vehicle having an exoskeleton that forms an outer shape and has rigidity.
2. The floating type according to claim 1, wherein the exoskeleton is configured to include a planar partition structure that is formed into a planar shape having a predetermined thickness and is partitioned into a plurality of spaces by a plurality of walls. Flying body.
3. 3. The floating flying object according to claim 2, wherein the planar partition structure is configured by a honeycomb structure having a plurality of hexagonal structures each having a hexagonal cross-sectional shape extending in a thickness direction.
4. 4. The levitated flying vehicle according to claim 2, wherein the exoskeleton has a core member disposed inside the planar partition structure and supporting the planar partition structure.
5. The floating flying object according to any one of claims 1 to 4, further comprising a reinforcing member that protrudes from the exoskeleton body to a side of the exoskeleton body to reinforce the exoskeleton body.
6. The levitation aircraft according to any one of claims 1 to 5, wherein the levitation body has an outer peripheral edge formed in an acute angle shape in a side view.
7. One or more of the levitation bodies,
   The levitation-type flying body according to any one of claims 1 to 6, wherein a thin portion serving as a wind passage in the horizontal direction is formed in at least two directions.
8. The levitation body is formed by sealing a gas having a specific gravity smaller than air inside,
   The levitation machine further includes a plurality of air sac bodies formed by being disposed inside the exoskeleton body and surrounded by a resin-like film so as to partition the inside of the exoskeleton body into a plurality of air chambers. The floating type flying body according to any one of 1 to 7.
9. The levitation body according to claim 8, wherein the levitation body further includes an outer air sac body that is disposed between the exoskeleton body and the plurality of air sac bodies and is formed in a substantially same shape as the exoskeleton body by a resin-like film. Type flying object.

Images