JP5811384B1 - Air levitation device and its air navigation - Google Patents

Abstract

An air levitation device that reduces energy consumption and enables low-cost, long-term observation. An air levitation apparatus (1) includes a fuselage body (2), an aircraft wing-shaped structure (3), an angle controller (4) for controlling the angle of the aircraft wing-shaped structure (3), and an automatic controller (8) for the angle controller (4). And the GPS 9, the wind direction wind measuring device 5 and the wind direction rudder 6, and the automatic control device 8 descends the body body 1 according to the data of the aircraft height and flight distance by the GPS 9, the wind direction wind measuring device 5 and the wind direction rudder 6. And the timing of the ascent, and the angle controller 4 autonomously controls the angle of the wing-shaped structure 3 of the aircraft, and the aircraft body 2 is driven by the propulsive force of the lift, drag and gravity of the wing-shaped structure 3 of the aircraft. Is lowered and raised, and the position in the air is always maintained within a predetermined range by reciprocating the two upper and lower region ranges. [Selection] Figure 1

Description

  The present invention relates to an air levitation device and its air navigation.

  Conventionally, for example, a radiosonde is known as an air levitation device for weather observation. A radiosonde is a meteorological observation device with a radio that is mainly blown by a rubber balloon to observe meteorological data (temperature, humidity, atmospheric pressure) from the ground up to an altitude of about 30 km.

  However, the radiosonde cannot maintain a fixed position in the air for a long time. This is because a radiosonde is usually attached to a rubber balloon and observes the temperature, humidity, and pressure of the sky as it rises.

  For the purpose of weather observation, an apparatus capable of maintaining a fixed position is desired. However, for example, in a method of maintaining a fixed position by a thrust of an aircraft gasoline internal combustion engine, fuel is consumed and a fixed point cannot be maintained for a long time. Further, the method of maintaining the fixed point by rotating the propeller by the motor driven by sunlight cannot be maintained at night. In addition, the battery charging method has problems such as an increase in the weight of the battery and an increase in cost due to the battery life, and a problem that it cannot cope with a long-time operation.

  In Patent Document 1, a propeller that generates lift is rotated by a motor, and a movable wing that tilts a machine body that rotates in a direction opposite to the propeller in response to the rotation reaction force in a predetermined tilt direction and a rotating machine body 2 are synchronized. A meteorological observation device is described that includes a tail wing that operates periodically, moves the aircraft to an arbitrary aerial position, and maintains a fixed point.

JP 2012-083318 A

However, the device of Patent Document 1 requires not only a complicated mechanism for controlling the rotor blades, movable blades, and tail blades, but also requires electric power for the motor that supplies the rotational power. Therefore, it is not a simple and low-cost device for long-term observation.
On the other hand, it is known that when a wind is applied to an aircraft-shaped object, a propulsive force composed of lift, drag and gravity is generated. The present invention makes use of this to enclose hydrogen or helium gas in an airtight wing-shaped airtight container to obtain a levitation force, and to provide a propulsive force by a solar power generation system and to provide a horizontal angle of the wing-shaped airtight container. By automatically controlling the wind direction or wind force, it is possible to move up and down in the air and stay in a certain range in the air, thereby reducing energy consumption and performing long-term aerial fixed-point weather observation at low cost It is an object of the present invention to provide an air levitation device that can be equipped with an aerial fixed-point radio antenna for relaying radio waves and an aerial fixed-point camera for long-time observation.

In order to solve the above-mentioned problems, the invention of claim 1 is directed to an airframe body, an aircraft wing-shaped structure, an angle controller that controls a relative angle between the wing-shaped structure and an air current, and an automatic angle controller. A control device, a GPS, a wind direction wind measuring device and a wind rudder, and the automatic control device controls the descending and raising of the body by the GPS altitude and flight distance, wind direction wind measuring device and wind rudder data. The timing is determined, the angle control machine autonomously controls the angle of the wing-shaped structure, the aircraft body is lowered toward the windward by the propulsive force consisting of lift and drag and gravity of the wing-shaped structure, and further downwind The aircraft body and the wing-shaped structure of the aircraft are connected to each other by the first rope. Mooring In addition, a vertical levitation body is moored by a second rope to the wing-shaped structure of the aircraft, and when the aircraft body is lowered toward the windward, the second levitation body When the mooring rope is loosened and the vertical levitation body is in a state of blowing wind, it is lowered with the aircraft wing-shaped structure and the main body, and when the main body is raised toward the leeward, the second mooring of the vertical levitation body The rope is tightened to control the angle so that the saddle-type levitation body can obtain a propulsion force composed of lift force, drag force, and gravity, and is raised together with the wing-shaped structure body and the airframe body of the aircraft .
According to a second aspect of the present invention, the wing-shaped structure of the aircraft is formed in a sealed container structure, and hydrogen or helium gas is enclosed therein, and the air levitation device includes the pressure vessel for refilling the hydrogen or helium gas. In addition, the automatic control device controls the replenishment or discharge of hydrogen or helium gas according to the data of the wind direction and wind measuring device, and the position in the air when no wind is present is always maintained within a predetermined range.
In the invention of claim 3, the aerial levitation apparatus is further provided with propulsion power by a solar power generation system, and the solar levitation apparatus is propelled by the solar power generation system at the time of no wind or in a light breeze close to the no wind. The amount of helium gas replenished or discharged and moved to the leeward is moved toward the windward by the propulsion power of the photovoltaic power generation system and returned to the original position during the daytime. It is characterized in that the airspace is maintained within the range.
The invention of claim 4 is further characterized in that the saddle-type levitation body is a hang glider.
The invention according to claim 5 is characterized in that the saddle type floating body is a paraglider.
The invention of claim 6 is an air levitation method for an air levitation device for staying in a certain range in the air using wind power without using human power or an internal combustion prime mover. Wing-shaped structure, an angle controller that controls the relative angle between the wing-shaped structure and the airflow, an automatic controller for the angle controller, GPS, a wind direction wind measuring instrument, and a wind rudder And the flight distance, wind direction wind measuring instrument and wind direction rudder data, the automatic control device determines the descent and rise timing of the fuselage body, and the angle controller autonomously controls the angle of the wing shape structure, and the wing shape Position in the air by lowering the aircraft body upwind by the propulsive force consisting of lift and drag of the structure and gravity, and then raising it up and down and reciprocating the two upper and lower area ranges Characterized in that to hovering always maintained at a predetermined range, the levitation method the levitation device, balloons or aircraft, and the predetermined highly pulling step by other flotation means consisting of rocket, other flotation airborne device When there is a predetermined air flow in the atmosphere separated from the means, the automatic control device determines the descent and ascent timing of the aircraft body based on the aircraft altitude and flight distance by GPS, wind direction wind measuring instrument and wind direction rudder data The angle control unit autonomously controls the angle of the wing-shaped structure or saddle-type levitation body, and the propulsive force of the wing-shaped structure or saddle-type levitation body always maintains the position in the air within a predetermined range. When there is no predetermined air flow in the atmosphere, hydrogen or helium is added to the structure that the automatic controller uses as a sealed container for the air levitation device based on the data of the wind direction wind measuring device. Supplemented scan, characterized in that it comprises the step of maintaining the position at all times a predetermined range in the air by making the propulsion by the discharge control, and / or solar systems.

  According to the present invention, by maintaining the air position of the levitating device over a long period of time, energy observation can be performed for weather observation, radio wave relay, image of a fixed point camera, and video observation at a continuous fixed position for 24 hours 365 days. And can be realized at low cost.

It is a schematic diagram which shows the 1st Embodiment of this invention. It is a schematic diagram which shows the vector of the force applied to a wing | blade shape structure on a cross section, and shows the case where an air levitation device receives a crosswind and is falling. It is a schematic diagram which shows the vector of the force applied to a wing | blade-shaped structure on a cross section, and shows the case where an air levitation device receives a crosswind and is rising. It is a schematic diagram which shows the angle of the wing | blade shape structure body of the air levitation apparatus which raises and descends in response to a cross wind, (a) shows the state at the time of a fall, (b) shows the state at the time of a raise. It is a schematic diagram of an air levitation device that rises and descends in response to a crosswind from the ground, showing the rise to the leeward under propulsion, and the fall to the upwind under free fall and propulsion . It is a schematic diagram which shows the 3rd Embodiment of this invention, and is an Example which uses a saddle type plane levitation body. (A) shows a state when descending, and (b) shows a state when ascending. It is a schematic diagram which shows the 3rd Embodiment of this invention, and is an Example using a paraglider. (A) shows a state when descending, and (b) shows a state when ascending. It is a schematic diagram which shows the 4th Embodiment of this invention, and is an Example which uses a saddle type plane levitation body. (A) shows a state when descending, and (b) shows a state when ascending.

Hereinafter, a first embodiment of the present invention will be described with reference to the drawings. First, the configuration of the present embodiment will be described. Note that observation equipment and the like mounted on the levitating apparatus 1 are not shown.
As shown in FIG. 1, the levitating apparatus 1 includes a fuselage body 2, an aircraft wing-shaped structure 3, an angle controller 4 that controls the angle of the wing-shaped structure 3, and automatic control of the angle controller 4. A device 8, a GPS 9, a wind direction wind measuring instrument 5 and a wind direction rudder 6 are provided.
In the present embodiment, two wing-shaped structures 3 are arranged symmetrically in the horizontal direction.

  The wing-shaped structure 3 is attached to the airframe body 2 so that the angle can be adjusted. The wing-shaped structure 3 is connected to the angle controller 4, and the wing angle is mechanically and autonomously controlled by a command from the automatic control device 8, so that no radio instruction from the ground is required.

  A simple interlocking method may be used in which a mechanical interlocking mechanism is provided between the wind direction and wind force measuring instrument 5 and the wing-shaped structure 3, and the angle control of the wing-shaped structure 3 is limited to several patterns. In the body 2, the above devices are arranged so as to maintain a basic aerial posture like a badminton shuttlecock in consideration of the position of the center of gravity.

Next, the air navigation using the air levitation apparatus of the present embodiment will be described with reference to FIGS.
First, the air levitation device 1 is released to an observation position at an appropriate atmospheric altitude by a balloon, an aircraft, a rocket, or the like.

Next, a description will be given of the aerial navigation of the present invention in which the air levitation apparatus 1 that is basically levitated to a certain altitude by the above-described method is held at a certain position against a change in wind direction and wind speed for a long time.
The position balance in the vertical direction of the levitating device 1 is inevitably lost depending on the atmospheric pressure, temperature, and wind direction. That is, the air levitation device 1 performs a downward or upward movement, and at that time, the air levitation device 1 receives wind relatively upward or downward from the atmosphere. In this case, first, the air levitation device 1 is rotated horizontally around the vertical axis by the wind rudder 6 so that the wing-shaped structure 3 receives the cross wind from the front surface of the wing shape as shown in FIGS. The angle adjustment of the wing-shaped structure 3 and the movement of the air levitation device 1 will be described below.

  FIG. 2 shows an aircraft wing when the air levitation apparatus 1 receives a relatively upward wind due to a downward movement, and receives a normal crosswind due to atmospheric conditions and receives an obliquely upward wind as a whole. The force which the shape structure 3 receives is shown.

  When receiving a wind that is obliquely upward as the relative air flow shown in FIG. 2, the wing-shaped structure 3 whose angle is adjusted obliquely downward so that the tip side of the wing shape faces the windward has a drag D in a direction parallel to the wind. A lift L is generated perpendicular to this and directed to the upper part of the wing. As the wing shape of the wing-shaped structure 3, a shape in which the drag D is small and the lift L is large is selected.

  In addition to this, gravity W shown in FIG. 2 acts on the wing-shaped structure 3, and this force is a vertically downward force W. Assuming that the resultant force of the drag D and the gravity W is a force A, the resultant force of the force A and the lift L is a resultant force of all forces acting on the wing-shaped structure 3. This vector sum A + L is called the propulsive force T of the wing-shaped structure 3. In this case, it can be seen that the propulsive force T is directed downward and upwind.

  FIG. 3 shows the wing of an aircraft when the levitating device 1 moves upward and receives a relatively downward wind, and receives a normal crosswind due to atmospheric conditions and receives an obliquely downward wind as a whole. The force which the shape structure 3 receives is shown.

  When receiving a wind that is obliquely downward as the relative air flow shown in FIG. 3, the wing-shaped structure 3 whose angle is adjusted obliquely upward so that the tip side of the wing shape faces the windward has a drag D in a direction parallel to the wind. A lift L toward the upper part of the wing is generated perpendicular to the wind. In addition to this, gravity W is acting on the wing-shaped structure 3, and the force W is vertically downward. Assuming that the resultant force of the drag D and the gravity W is a force A, the resultant force of the force A and the lift L is a resultant force of all forces acting on the wing-shaped structure 3. This vector sum A + L is called the propulsive force T of the wing-shaped structure 3. In this case, it can be seen that the propulsive force T is directed upward and leeward.

When the wing angle of the wing-shaped structure 3 is switched from the state of FIG. 2 to the state of FIG. 3, the positional relationship between the airframe body 2 and the wing-shaped structure 3 of the air levitation device 1 is as follows when the air levitation device 1 is lowered. FIG. 4A changes as shown in FIG. 4B when the levitating device 1 is raised.
In FIGS. 1 and 4 (a), the wing-shaped structure 3 of the aircraft is used in a state where the aircraft wing-shaped structure 3 is set up at an angle close to the vertical to the body 2 like a sail of a yacht. (See FIG. 2) is mainly for advancing the fuselage body 2 to the windward. On the other hand, in FIG. 4B, the wing-shaped structure 3 of the aircraft is used at an angle close to horizontal like the main wing of the aircraft with respect to the main body. The lift L (see FIG. 3) at this time is mainly used for raising the body 2.
In FIG. 4 (b), the aircraft rises toward the leeward due to the lift by the airflow relative angle, but due to the movement toward the leeward, the lift is gradually lost and balances with gravity. At this time, when only the drag force is reached, the aircraft changes from rising to FIG. 1 and FIG. 4 (a) in order to obtain the airflow relative velocity.

In the state of FIG. 4 (a), after obtaining the relative velocity of the air flow by increasing the speed due to free fall, the lift increase in FIG. 4 (b) from the state of moving toward the windward by gliding toward the windward By repeatedly switching the angle of the wing-shaped structure 3 of the aircraft to the state of moving to the leeward by ascending due to ascending and further to the state of FIG. On the ground, the vertical movement is repeated in an oblique direction when viewed from the side, so that it can stay in a certain range in the air.
The wing angle is switched based on the GPS body height and flight distance information.
Note that the GPS received power energy and the wing angle are switched by the photovoltaic power generation panel, power storage from the photovoltaic power generation panel, or wind energy.

  Here, unlike the present embodiment, the air levitation device 1 is configured with only a single leaf, that is, a single aircraft wing-shaped structure 3 or a configuration in which only one row of wing-shaped structures 3 is arranged vertically. Since the cross-sectional shape of the wing differs depending on the position of the wing, in addition to the up and down movement in the oblique direction of FIG. 4, even when viewed from directly above, it moves in a zigzag manner like a yacht toward the windward. In the case of this embodiment, since it is a multi-leaf arrangement in which the wing-shaped structures 3 are arranged symmetrically on the left and right, the propulsive force by the left and right wing-shaped sealed containers 3 is balanced in the left-right direction and synthesized. Goes straight upwind, and there is no zigzag movement when viewed from directly above, and only up and down movement in the oblique direction shown in FIG.

Next, a second embodiment will be described.
The outer shape of the aircraft wing-shaped structure 3 of the present embodiment has the shape of an aircraft wing, and is a confidential structure in which hydrogen gas or helium gas is sealed. The hydrogen or helium gas replenishment pressure vessel 7 is connected to each blade-shaped structure 3 by a flexible pipe (not shown), and the pressure valve 10 is used to adjust the amount of gas filled in the blade-shaped structure 3 to adjust the blade-shaped structure 3. The buoyancy of the body 3 is adjusted.

Unlike the first embodiment, the air levitation device 1 of the present embodiment can maintain a constant altitude even when a predetermined air flow does not exist in the space where the air levitation device 1 floats. That is, when there is no wind or when the wind is blowing less than the predetermined wind speed, the automatic control device 8 performs control to replenish or discharge hydrogen or helium gas to the wing-shaped structure 3 based on the data of the wind direction wind measuring device 5. It is possible to always maintain the air position within a predetermined range. Specifically, when increasing the buoyancy, hydrogen or helium gas is replenished to the sealed container 3 from the replenishing pressure vessel 7, and when reducing buoyancy, hydrogen or helium gas is released from the sealed container 3 to the atmosphere and floated in the air. The total weight of the device 1 and the buoyancy due to hydrogen or helium gas sealed in the sealed container 3 are balanced, and adjustment is performed to suppress the vertical movement of the air levitation device 1 as much as possible. In addition, a solar power generation system (not shown) is mounted on the levitating apparatus 1 of the present embodiment, and the distance moved to the leeward nighttime can be determined by the solar power generation system during the daytime even in the case of a breeze below a predetermined wind speed. The propulsion force generated by the rotation of a motor (not shown) can be advanced toward the windward and returned to the original position, so that the position of the airframe in the air can always be maintained within a predetermined range.
When wind of a predetermined wind speed or higher is blowing, the air position is always maintained within a predetermined range by controlling the angle of the wing-shaped structure 3 as in the first embodiment.

Next, a third embodiment will be described.
In the present embodiment, as shown in FIG. 6, the airframe body 2 and the aircraft wing-shaped structure 3 are moored by the first rope 14, and the aircraft wing-shaped structure 3 further has a saddle type plane levitation. When the body 11 is moored by the second rope 15 and the airframe body 2 is lowered toward the windward, the second mooring rope of the saddle type plane levitation body 11 as shown in FIG. 15 is loosened, and the vertical levitation body 11 is in a state of blowing wind. After obtaining the airflow relative velocity by free fall together with the wing-shaped structure 3 and the aircraft body 2 of the aircraft, it is glide down toward the windward.
When raising the airframe body 2 toward the leeward side, the second mooring rope 15 of the saddle type plane levitation body 11 is tightened as shown in FIG. The angle is controlled so that lift is obtained, and at the same time, the wing-shaped structure 3 is also raised together with the body 2 by switching the airflow relative angle of the wing to an angle at which maximum lift is obtained.

As described above, when the airframe body 2 is further glide down toward the windward from the free fall, the angle of the vertical plane levitation body 11 is adjusted by adjusting the second mooring rope 15 in the vertical plane levitation body 11. The aircraft is lowered toward the windward by the wing-shaped structure 3 of the aircraft adjusted to an angle that suppresses drag and lift.

When the airframe body 2 is raised toward the leeward side, the vertical mooring body 11 receives the wind by tightening the second mooring rope 15 so that the vertical mooring body 11 receives the wind. 11 is controlled to an angle at which drag and lift are increased, and is raised toward the lee side together with the wing-shaped structure 3 and the main body 2 of the aircraft.
In this embodiment, the aircraft wing-shaped structure 3 is fixed at a predetermined angle in advance, and the airborne position of the airframe body 2 is always set by controlling only the airflow relative angle of the saddle type plane levitation body 11. It is also possible to keep the airspace within a predetermined range.

  Further, even if a hang glider 12 or a paraglider 13 (see FIG. 7) is used instead of the saddle type plane levitation body 11, the air levitation apparatus 1 can always be maintained in a predetermined range in the air by the same navigation as described above. it can. In the case of the paraglider 13, the second mooring rope 15 is adjusted so that the drag and lift are reduced as much as possible in the paraglider 13 when free-falling and glide down toward the windward.

Next, a fourth embodiment will be described.
In the present embodiment, the air levitation device 1 includes an airframe body 2, a vertical plane levitation body 11, an angle controller 4 that controls the relative angle between the vertical levitation body 11 and the airflow, and an automatic angle control device 4. A control device 8, a GPS 9, a wind direction wind measuring device 5 and a wind direction rudder 6 are provided, and the body body 2 descends and rises according to data of the aircraft height and flight distance by the GPS 9, the wind direction wind measuring device 5 and the wind direction rudder 6. The angle controller 4 controls the angle of the vertical plane levitation body 11, and the aircraft body 2 is lowered toward the windward by the propulsive force consisting of the lift and drag and gravity of the vertical plane levitation body 11, Furthermore, it raises toward the leeward and reciprocates the two upper and lower area ranges, so that the position in the air is constantly maintained within a predetermined range.

Unlike the above-described first to third embodiments, the levitating apparatus 1 according to the present embodiment does not include the aircraft wing-shaped structure 3 and is directly attached to the main body 2 as shown in FIG. The levitation body 11 is moored by a third mooring rope 16.
Although omitted in FIG. 8, the airframe body 2 is equipped with an apparatus similar to that of the first embodiment below the angle controller 4, and the angle controller 4 controls the angle of the saddle type plane levitation body 11. And the position in the air of the levitating apparatus 1 is always maintained in the predetermined range by the navigation similar to the 1st-3rd embodiment.

  Specifically, when the airframe body 2 is glide down toward the windward, as shown in FIG. 8 (a), the third mooring rope 16 is adjusted to change the angle of the saddle type plane levitation body 11, The propulsive force T, which is the combined force of the lift L force, the drag force D, and the gravity W, is made to be in a direction to glide down toward the windward.

Further, when the airframe body 2 is raised toward the leeward side, as shown in FIG. 8 (b), the third mooring rope 16 is adjusted so that the angle of the vertical plane levitation body 11 is changed to the lift L and the drag D. The propulsive force T, which is the combined force of gravity W, is made to rise in the direction toward the leeward.
Also in the present embodiment, the levitation apparatus 1 is always maintained in a predetermined range in the air by using the hang glider 12 and the paraglider 13 (see FIG. 7) instead of the saddle type plane levitation body 11 by the navigation similar to the above. Can be made.

  With the configuration and function as described above, the levitating apparatus of the present embodiment can maintain a constant position and altitude in the air even when the wind direction changes in wind speed or changes in temperature and pressure. Realizes meteorological observation at locations, radio wave relay, image and video observation with fixed-point cameras with low energy consumption and low cost.

Below, the air levitation apparatus of the present invention is compared in detail with a conventional levitation apparatus such as an airship to confirm the effect.
According to the fixed-point aerial test on the airship, the aircraft is levitated in the stratosphere (altitude 20 km to 25 km) with little influence of weather. However, the region where the influence of weather is small means that the airship has little buoyancy, and the hull must be enlarged accordingly. Therefore, according to a report from the Japan Aerospace Exploration Agency, a huge airship with a total length of 200 meters is required for the size of the ship to be suspended in the stratosphere. When it becomes such a huge hull, the hull weight reaches several tons without helium gas.

  It is also known that the frame and membrane materials that support the huge hull are expensive, and that there are no weather conditions throughout the year until launching into the stratosphere. It can be easily guessed that an advanced control mechanism is necessary even if the airship's nose is always directed upwind. If the launch of the hull depends on the weather, it will be a condition that cannot be accepted as a business because it is costly and a schedule is not planned.

In the conventional technology, there is a levitation body that observes the weather with a radiosonde, but the fixed point cannot be maintained. In addition, the thrust generated by the gasoline internal combustion engine of an aircraft consumes fuel and cannot maintain a fixed point for a long time. Furthermore, the fixed point maintenance by the motor driven by sunlight cannot be maintained at night, and the method of charging the battery cannot increase the cost or operate for a long time due to the increase of the battery weight or the battery life.
In addition, the airship type is used in the stratosphere where there is little influence of the weather, but at the same time, there is no buoyancy, so it becomes a huge airship, cost is high, and launching to the stratosphere is difficult.

With respect to these problems, the air levitation apparatus of the present invention focuses on the following as the principle of levitation.
That is, in the wing shape of the aircraft, a lift proportional to the square of the wind speed relative to air can be obtained. When there is a wind, the lift and drag can be controlled by the "attack angle" by adjusting the "attack angle" relative to the wind direction with the wings facing upwind, and the balance between lift and gravity. The aircraft can be advanced in the direction of synthesis, which is conventionally called “glide”. At this time, a propulsive force toward the windward is generated by the release of potential energy due to the descent of the aircraft.
The magnitude of the combined force as the driving force is equal to the drag, and the direction is upwind. After traveling a certain distance upwind, the wing's “attack angle” is adjusted to increase with maximum lift, and the lift increases with the increased lift. The remainder of the lift minus the gravitational force is the ascending force, and the aircraft rises. The upward driving force is combined with the drag force, and the direction is leeward. By repeating ascending and descending so that the distance toward the windward and leeward is the same, it becomes an aerial sky with a fixed range maintained. This is the method used in the first embodiment of the present invention described above.
In addition, there is a conventional aerial flight method called “soaring”, but compared with the present invention, the relationship between the moving direction of the device and the windward and leeward is reversed. The present invention is different from the present invention in that it cannot stay in the air.

  The lift is generated not only in the wing-shaped structure of an aircraft but also in a kite type. Kite always receives drag from the relative airflow in the downstream direction. If the flow is asymmetrical due to the shape of the object and the direction to the flow, if there is a pressure difference in the direction perpendicular to the flow due to Bernoulli's theorem due to the difference in flow velocity, lift occurs in that direction. Similar to the kite type, hang gliders and paragliders can fly in the air on the same principle. In the fourth embodiment described above, only the kite type, hang glider or paraglider is used without using the wing-shaped structure.

  A fixed-point aerial suspension is also achieved by the three-body integrated structure of the aircraft wing-shaped structure with the wing angle of attack set in advance under the gliding conditions according to the aircraft body and the wind speed, and the saddle-type levitation body moored with a rope from there. Is possible. In this case, rotation of the wing is not necessary. When the aircraft body is glide down toward the windward, the mooring rope of the saddle-like levitation body is loosened so that the saddle-type levitation body blows the wind, and the wing-shaped structure of the aircraft is integrated with the gliding state. And glide. When raising the fuselage body toward the leeward, the rope from the wing-shaped structure of the aircraft to the saddle-like levitation body is tightened so that the wind-like levitation body can receive the maximum lift by the wind speed. The angle is controlled and the wing-shaped structure that has been set to the fixed glide angle in advance by the wind speed and the aircraft body are raised together with the aircraft body, and the ascent and descent are repeated so that the distance toward the windward and leeward is the same. Airborne. The saddle-like levitation body can be suspended in the air on the same principle whether it is a hang glider or a paraglider. This is the method described as one example of the above-described third embodiment.

  Unlike the conventional airship, the air levitation apparatus of the present invention obtains energy stagnated by wind power, so that it becomes more stable, for example, when there is a westerly wind that always exists in a certain area called a jet stream. The fixed position in the air is suspended over a long period of time by the lift and drag of the levitating body and the propulsive force obtained by gravity. Compared to an airship, a much smaller, lighter and lower cost airframe can be manufactured. For 24 hours, 365 days, weather observation at a fixed point, images with a fixed point camera, and moving image observation reduce energy consumption and enable long-term air suspension at a low running cost.

1 Air levitation device
2 Airframe body
3 Aircraft wing shape structure 4 Angle controller
5 Wind direction wind measuring instrument
6 Wind rudder
7 Refill pressure vessel
8 Automatic control device
9 GPS
10 Pressure valve
11 Vertical Floating Body 12 Hang Glider 13 Paragliding 14 First Mooring Rope 15 Second Mooring Rope 16 Third Mooring Rope

Claims (6)

An air levitation device for staying in a certain range in the air using wind power without using human power or an internal combustion prime mover, the air levitation device,
The aircraft body,
An aircraft wing-shaped structure,
An angle controller for controlling the relative angle between the airfoil structure and the airflow;
An automatic control device of the angle controller;
A GPS, a wind direction wind measuring instrument and a wind rudder,
The automatic controller determines the descent and ascent timing of the fuselage main body based on the GPS altitude, flight distance, wind direction wind measuring instrument, and wind direction rudder data, and the angle controller controls the angle of the wing-shaped structure. The aircraft body is lowered toward the windward by the propulsive force consisting of lift, drag and gravity of the wing-shaped structure, and is further lifted toward the leeward, and the two upper and lower areas determined. By reciprocating the range, the position in the air is constantly kept in the predetermined range ,
The aircraft body and the aircraft wing-shaped structure are moored by a first rope,
The saddle-type levitation body is further moored by a second rope to the wing-shaped structure of the aircraft,
When lowering the fuselage body toward the windward,
Loosen the mooring rope and let the vertical levitation body blow the wind.
Lower with the wing-shaped structure and the aircraft body,
When the aircraft body is raised toward the leeward side, the second mooring rope of the vertical levitation body is tightened to control the angle so that the vertical levitation body can obtain a propulsion force consisting of lift, drag and gravity. And lift together with the wing-shaped structure of the aircraft and the aircraft body,
An air levitation device characterized by that.   The aircraft wing-shaped structure is formed in a sealed container structure, in which hydrogen or helium gas is sealed, and the air levitation device includes the hydrogen or helium gas replenishment pressure vessel, and the wind direction wind measuring instrument The automatic control device controls the replenishment or discharge of the hydrogen or helium gas based on the data of the above, so that the position in the air during no wind is always maintained within a predetermined range. Air levitation device.   The said levitating apparatus is equipped with a solar power generation system, The position in the air is always maintained in a predetermined range by propelling the said levitating apparatus at the time of no wind by this solar power generation system, It is characterized by the above-mentioned. Or the levitating apparatus of 2. The air levitation apparatus according to any one of claims 1 to 3, wherein the saddle-type levitation body is a hang glider. The air levitation device according to any one of claims 1 to 3, wherein the saddle-type levitation body is a paraglider. An air levitation method of an air levitation device for staying in a certain range in the air using wind power without using human power or an internal combustion prime mover, wherein the air levitation device is
The aircraft body,
An aircraft wing-shaped structure,
An angle controller for controlling the relative angle between the airfoil structure and the airflow;
An automatic control device of the angle controller;
A GPS, a wind direction wind measuring instrument and a wind rudder,
The automatic controller determines the descent and ascent timing of the fuselage main body based on the GPS altitude, flight distance, wind direction wind measuring instrument, and wind direction rudder data, and the angle controller controls the angle of the wing-shaped structure. The aircraft body is lowered toward the windward by the propulsive force consisting of lift, drag and gravity of the wing-shaped structure, and is further lifted toward the leeward, and the two upper and lower areas determined. By reciprocating the range, the position in the air is constantly maintained in the predetermined range,
The air levitation method uses the air levitation device,
Step up to a predetermined altitude by other levitation means consisting of balloons, aircraft, rockets,
Separating the air levitation device from the other levitation means;
When a predetermined air flow exists in the atmosphere, the automatic control device determines the timing of the lowering and raising of the airframe body based on the data of the airframe altitude, flight distance, wind direction wind measuring instrument and wind direction rudder by the GPS. The angle control unit autonomously controls the angle of the wing-shaped structure or the saddle-type levitation body, and the position in the air is always set to a predetermined position by the propulsive force of the wing-shaped structure or the saddle-type levitation body. Keep it in range,
Control where the automatic control device replenishes and discharges the hydrogen or helium gas to the structure as a sealed container of the air levitation device according to the data of the wind direction and wind measuring instrument when there is no predetermined air flow in the atmosphere, And / or a step of constantly maintaining the position in the air in a predetermined range by performing the propulsion by the solar power generation system, and an air levitation method for an air levitation device.

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