KR0169708B1 - Aircraft and method of flying the same - Google Patents

Abstract

An object of the present invention is to provide a vehicle that can improve the running speed and prevent the fall even when the propeller stops generating propulsion. The wing, a bladder made of a flexible material, is installed at the top of the fuselage and filled with gas with a specific gravity lighter than air. In addition, a propeller is installed in the aircraft body.

Description

Aircraft and flying method of the aircraft

1 is a plan view of a vehicle 11, which is an embodiment of the present invention.

2 is a vertical sectional view of the main blade 12.

3 is a perspective view of the vehicle 11.

4 is a vertical cross-sectional view of an aircraft main wing 50 which is another embodiment of the present invention.

5 is a plan view of a vehicle 21, which is another embodiment of the present invention.

FIG. 6 is a side view of the vehicle 21 shown in FIG.

7 is a plan view of a vehicle 23, which is another embodiment of the present invention.

8 is a perspective view of an aircraft 25 which is another embodiment of the present invention.

9 is a perspective view of an aircraft 28 which is another embodiment of the present invention.

10 is a perspective view of a vehicle 35, which is another embodiment of the present invention.

11 is a longitudinal cross-sectional view of the vehicle 35 shown in FIG.

FIG. 12 is a plan view of the vehicle 35 shown in FIG.

13 is a perspective view of another embodiment of the present invention.

14 is a perspective view of an aircraft 45 which is another embodiment of the present invention.

15 is an axial orthogonal cross-sectional view of the fuselage 14 which is another embodiment of the present invention.

16 is a perspective view of an aircraft 110, which is another embodiment of the present invention.

17 is a front view of the vehicle 110.

18 is a plan view of the vehicle 110.

19 is a side view of the vehicle 110.

20 is a side view of the aircraft 150 which is another embodiment of the present invention.

21 is a perspective view of a mechanism 1 of the prior art.

22 is a perspective view of another prior art instrument 4.

23 is a perspective view of a prior art aircraft.

The present invention relates to flying a flying vehicle in the air.

A typical prior art is the instrument 1 shown in FIG. The instrument 1 comprises a spherical envelope (2) filled with a gas which is lighter than the specific gravity of the air and a carrying basket 3 suspended in the bladder to pick up the driver.

Another prior art depicted in FIG. 22 describes an instrument 4 consisting of an oval bladder filled with gas with a specific gravity lighter than air and a carrying basket suspended in the bladder to burn the driver.

In the prior art shown in FIGS. 21 and 22, the traveling speed of the mechanism cannot be improved because the instruments 2, 5 are spherical or elliptical. In addition, in these prior arts, there is no consideration for increasing the buoyancy or lift of the mechanism by wind or the like.

23 is a perspective view of another prior art. The prior art relates to an airplane, in which a propeller 8 is rotated to obtain propulsion and lift by a wing.

In an airplane of the kind shown in FIG. 23, when the propeller 8 fails, lift is not generated by the wings 9, causing a very large accident such as a fall.

An object of the present invention is to provide a vehicle that can improve the running speed and prevent the fall when the propeller cannot provide propulsion to the vehicle.

The invention is characterized in that the aircraft has wings filled with a gas having a specific gravity lighter than air.

In addition, the present invention is characterized in that the wing is installed on the upper part of the body.

In addition, the present invention is characterized in that the propulsion force generation means is provided in the fuselage or the wing.

Further, the present invention is characterized in that the propulsion force generating means includes a propeller and an internal combustion engine for driving the propeller.

In addition, the present invention is characterized in that the propulsion force generating means is a jet engine.

In addition, the present invention is characterized in that the gas is natural gas, helium or the like.

In addition, the present invention is characterized in that the wings are air sacs made of a flexible material. In addition, the present invention is characterized in that the aircraft has a sliding foot for sliding in the water or underwater.

In addition, the present invention is characterized in that the buoy is installed on the upper part of the body is filled with a gas of specific gravity lighter than air.

The vehicle according to the present invention has a space extending along the longitudinal direction of the fuselage, characterized in that the gas is filled with a specific gravity lighter than air.

Aircraft according to the present invention has a wing, the inside of the wing is filled with a gas of a specific gravity lighter than air, for example, helium, neon or natural gas used as fuel to generate buoyancy in the wing. In addition, lift is generated when the wind is blowing, or when the propulsion force is generated by a propeller or jet engine, causing the aircraft to rise to a higher place.

Further, according to the present invention, it is possible to fly low to the ground or a place close to the sea level, which can save fuel of the propulsion generating means.

In the present invention as described above, since a gas having a specific gravity lighter than air is filled in the wing to generate buoyancy, the aircraft itself may be floated in the air in the same manner as in a conventional mechanism. In addition, by using such a wing, when the wind is blowing or the propulsion force is generated by the propulsion force generating means, the lift force can be generated to fly the aircraft. Therefore, it is possible to increase the flight speed and to prevent the fall even when the propulsion force generating means is broken.

In addition, according to the present invention, the natural gas can be transported from the mountain to the vehicle by filling the natural gas in the wing. Natural gas may be used as partially liquid, with more than 80% CH ₄ . The transport of natural gas by aircraft is safe because it is in the air in the event of a fire.

Other objects, features and advantages of the present invention will be described in detail with reference to the following detailed description and drawings.

1 is a plan view of an embodiment of the aircraft 11 of the present invention. In FIG. 1, the main body 14 is provided with a main wing 12, a tail wing 13, and a vertical tail wing 15. In addition, the driver body 16 is provided in the fuselage 14. In front of the vehicle body 14, a propeller 17 for generating propulsion force and an internal combustion engine 18 for driving the propeller 17 are provided.

2 is an axial vertical cross section of the main blade 12. The main wing 12 is a bladder made of a flexible material and has a shape in which the front surface 19 (left side of FIG. 1 or 2) is raised. The inner space of the main wing 12 is filled with a gas having a specific gravity lighter than air. Such a gas can be a rare gas such as helium, neon lamps, or a natural gas with a CH ₄ content of at least 80%. Natural gas may contain ethane, propane, butane, etc. in addition to methane. The main blade 12 is installed on the upper part of the body 14. Tail wing 13 and vertical tail wing 15 is determined by the main wing (12).

3 is a perspective view of the embodiment vehicle 11 shown in FIGS. 1 and 2. The vehicle 11 can be prevented from falling even when propulsion force cannot be obtained because the propeller 17 and the internal combustion engine can be suspended in the air even when the propeller 17 and the internal combustion engine are stopped. In addition, it is possible to ascend to a high altitude because lift is generated on the aircraft when the wind is blowing.

4 is a vertical cross-sectional view of the main wing 50 installed in another embodiment of the present invention. This embodiment is similar to the above embodiment, that is, the configuration except for the main wing 50 is the same. The main blade 50 of this embodiment is made of a material having rigidity such as synthetic resin and light metal (for example, aluminum alloy), and is formed to have an internal space. A bag 51 made of a flexible material is accommodated in the inner space, and the bag 51 is filled with a gas having a specific gravity lighter than air. Receiving the bag 51 in the main wing allows gas to be exchanged in the main wing 50. Optionally, such a bag can be housed in the body 41.

FIG. 5 is a plan view of another embodiment aircraft 21 of the present invention and FIG. 6 is a side view thereof. This embodiment is similar to the above embodiments. Corresponding parts have been given the same reference numerals. In this embodiment, the wings 12 are fixed on the body 14 so as to have a gap between the body 14.

7 is a plan view of another embodiment of the aircraft 23 of the present invention. The shape of the main blade 24 is different from that of the main wing 12. The plane shape of the main blade 12 is almost rectangular. However, the main wings 24 of the embodiment shown in FIG. 7 are nearly triangular.

8 is a perspective view of another embodiment aircraft 24 of the present invention. Aircraft 25 is similar to the embodiment shown in FIGS. Corresponding parts have been given the same reference numerals. The main wing is further provided with a vertical wing 26 to further increase the buoyancy and improve the ability to go straight.

9 is a perspective view of another embodiment of the present invention. The wing 28 of the present embodiment is provided with a wing 29 formed vertically between the main wing 12 and the tail wing 13. This configuration increases buoyancy and improves straight driving ability.

The vertical wing 26 of FIG. 8 protrudes outwardly from the main wing 12 in a plane-symmetrical configuration with respect to the plane of symmetry 30. The vertical wing 29 of FIG. 9 also projects outwardly from the main wing 12 as a configuration of face symmetry with respect to the symmetry plane 31. These vertical wings 29 and 29 are air sacs made of a flexible material and filled with gas having a specific gravity lighter than air.

In the embodiment shown in FIGS. 1 to 8, the body 14 is also filled with gas as air sacs made of a flexible material. In addition, the body 14 may be made of a rigid material such as metal or lightweight synthetic resin.

10 is a perspective view of another embodiment of the aircraft 35 of the present invention. 11 is a side view of the vehicle 35 shown in FIG. FIG. 12 is a plan view of the vehicle 35 shown in FIG. In this embodiment, the central vertical wing 32 and the left and right vertical wings 33 and 34 are installed between the main wing 12 and the tail wing 13. The main wing 12 and the tail wing 13 are disposed at the lower ends of the central vertical wing 32 and the left and right vertical wing 33, 34, respectively, the flat bottom (88-90), the tail wing of each of the main wing 12 (13), the central vertical wing 32 and the left and right wing 33, 34 are included in one coplanar 91. Also, the rear end of the main wing is at L5 distance from the front end of the tail wing 13. The left and right vertical wings 33 and 34 are arranged to be symmetrical and parallel to each other with respect to the vertical plane including the axis of the central vertical wing 32.

The tail wing 13 is smaller than the main wing 12 but formed almost similarly in the figure. Each upper part of the left and right vertical wings 33 and 34 is connected to the upper part of the central vertical wing 32 via the space connecting members 74 and 73 on the main wing 12, respectively. In addition, each upper portion of the left and right vertical wings 33 and 34 is connected to the upper portion of the central vertical wing 32 via the spatial connecting members 76 and 75 at a portion between the main wing 12 and the tail wing 13. . The connecting member 73-76 prevents the vertical wings from being separated due to the high air flow, thereby allowing steam to fly. Further, the rear ends of the vertical wings 32-34 coincide with the rear ends of the tail wings 13, which contribute to mutually increasing the strength of the tail wings 13 on the rear ends of the vertical wings 32-34. The main wing 12, the tail wing 13 and the vertical wing 32-34 each form a single space of air sealing. The upper and lower surfaces of each vertical wing 32-34 are formed flat and the horizontal section of each vertical wing 32-34 is the same in its vertical direction. Each vertical wing 32-34 is formed to have a streamlined shape. The horizontal cross-sectional front end 64 of the left and right vertical wings 32-34 has a round shape. In addition, each vertical wing (32-34) is formed so that the width of the horizontal cross-section has a streamline that gradually increases toward the upper portion of the main wing (12) from the front portion of the horizontal cross-section and gradually toward the upper portion of the tail wing (13) do. Accordingly, the distance L2 between the circumferential sides at the position where the horizontal plane width of the vertical blades 32-34 is maximum is the distance L3 at the front portion of the vertical blades 32-34 and the rear of the vertical blades 32-34. Smaller than the distance L4 in the part. In addition, the position of each vertical wing 32, 33, 34 closest to each of the vertical wings 33, 34 of the central vertical wing 32 coincides with the uppermost part of the main wing 12. As shown in FIG. In addition, the outer diameter D1 of the propeller 17 is equal to the distance L1 between the axes 94 and 95 of the left and right vertical wings 33 and 34. Therefore, the air flow rate that is increased by the propeller 17 is maximum at the positions 102 and 103 between the central vertical wing 32 and the left vertical wing 33 and between the central vertical wing 32 and the right vertical wing 34. This contributes to the generation of high lift. The axis of rotation of the propeller is disposed in the vertical plane and the horizontal plane 91 of the central vertical blade 32 including the shaft 93.

Each vertical wing 32-34 is formed to be an air sac of lightweight flexible material. In addition, the vertical wing (32-34) is filled with a gas of a specific gravity lighter than air, such as helium, neon and methane to improve buoyancy.

The vehicle 35 is driven by the internal combustion engine 63. The internal combustion engine 63 and the driver's seat 95 are disposed in a space in front of the central vertical wing 32 and the lower portion 94 of the internal combustion engine slightly protrudes from the bottom of the central vertical wing 32.

The left and right ends 85 and 86 of the tail wing 13 protrude beyond the left and right vertical wings 33 and 34, respectively, and the left and right ends 83 and 84 of the main wing 12 are similar to the left and right vertical wings 33. , 34, protrudes past.

FIG. 13 shows another embodiment of the present invention aircraft 37. As shown in FIG. The aircraft 37 includes a fuselage 14 provided with a main blade 38 which is a biplane. The body also has a tail wing that is also biplane. This configuration further increases buoyancy and lift.

The propeller 17 and the internal combustion engine 18 can be replaced by a jet engine. The vertical vanes 32, 33, 34 of FIG. 9, which can be expressed as a flotation, are face symmetric with respect to the vertical symmetry planes extending in the forward and backward directions of the aircraft fuselage.

The lower part of the fuselage 14 is provided with the traveling angle which has a wing-shaped vertical cross section which slides aquatic bodies or underwater. This type of travel angle allows the vehicle body 14 to travel lightly near the surface using high buoyancy.

14 is a perspective view of another embodiment of the present invention. This embodiment is similar to the embodiment shown in FIG. However, this embodiment has a remarkable feature in that the buoyant body 41 fixed to the upper part of the body 14 is cylindrical with spherical ends in the longitudinal direction. The support body 41 is filled with a gas having a specific gravity lighter than air. Other configurations are the same as those of the above-described embodiment.

15 is an axially vertical sectional view of the body 14 in yet another embodiment of the present invention. In the present embodiment, the body 14 of the above embodiment is divided into upper and lower spaces 43 and 44 by two parts, that is, the partition member 42. The upper space 43 is filled with gas having a specific gravity lighter than air. The upper space 43 is formed to be in the range of more than the total length of the body 14 along the longitudinal direction. The configuration of other parts of this embodiment is the same as the above embodiments. The type of configuration shown in FIG. 15 increases the buoyancy and lift of the vehicle.

In the embodiment shown in FIG. 14, a plurality of support bodies 41, for example, three support bodies as shown in FIG. 10, may be arranged in parallel with one another and fixed to the fuselage 14.

16 is a perspective view of another embodiment aircraft 110 of the present invention; 17 is a front view of the aircraft 110; 18 is a plan view of the aircraft 110; 19 is a side view of the vehicle 110. The body 111 of the aircraft 110 is made to be a substantially cylindrical streamlined diameter D. The axis 122 of the substantially cylindrical body 111 is directed in the flight direction A. The aircraft 110 is configured to be symmetric with respect to the virtual vertical plane 123 that includes the axis 122. The first main wing 112, which is flat and nearly triangular and has two rounded ends, is attached to be parallel to the axis of the fuselage 111. Both left and right ends of the first main wing 112 are formed to be annular, and the lower surface 112a of the first main wing 112 is disposed above the axis 122 of the body 111. The second main wing 113, which is similar in shape to the first main wing 112, is installed in parallel with the first main wing 112 at an interval (distance) H1 and upwards of the first main wing. Above the wing, the 3rd main wing 114 similar to the 1st main wing 112 by the space | interval (distance) H2 is provided in parallel with the 1st and 2nd main wing 112 and 113. As shown in FIG. The distances H1 and H2 are selected equal to each other.

The first main wing 112 and the second main wing 113 pass through a pair of vertical wings 119 disposed on the left and right of the vertical wing 116 and the vertical wing 116 disposed above the fuselage 111. Connected.

Each vertical wing 116, 117, 119, 120 is formed in a substantially elliptical cylindrical shape. The vertical wings 116 and 117 are arranged to be a first virtual elliptical cylindrical shape perpendicular to the first, second and third main wings 112-114. The vertical wings 119 and 120 are arranged to be a second virtual oval cylindrical shape perpendicular to the first, second and third main wings 112-114. The long axis of the ellipse, which is a cross section cut perpendicularly to the longitudinal axis of the vertical wings 116 and 117, is disposed parallel to the axis 122 of the body 111. The cross section cut vertically with respect to the longitudinal axis of the vertical wings 119 and 120 is arranged such that the long axis of the ellipse is parallel to the axis 122 of the body 111. Such a configuration improves straight flight. Further, the distance L11 between the imaginary surface 123 and the center of the vertical wing 119 is longer than the distance L12 between the center of the vertical wing 119 and the outer end of the main wing 12, preferably L11 is larger than L12. 1.5 times longer. Thus, the structural strength of the aircraft 110 is increased.

Upper vertical wing 118 is installed on the upper surface of the third main wing (114). The upper vertical blade 118 extends from the front end to the rear end in the traveling direction A side of the third main blade 114 so as to be parallel to the axis 122 of the body 111. At the rear end of the upper vertical wing 118, a vertical tail wing 124 extending upward is formed. The thickness T1 of the vertical tail wing 124 is formed thinner than the thickness T2 of the upper vertical wing 118, and the upper vertical wing 118 and the vertical tail wing 124 are integrally formed to be one body. The distance H1 from the first main blade 112 to the second main wing 113 is shorter than the distance H3 from the bottom of the upper vertical wing 118 to the bottom of the vertical tail wing 124 and the vertical tail wing 124. The distance from the top to the bottom of is longer than H4. Preferably the distance H3 is twice the length of the distance H4 and the distance H1 is 1.5 times longer than the distance H4. Thus, the safety during flight is improved. In addition, the thickness T ₂ of each of the vertical wings 116, 117, 119, and 120 is equal to the bottom thickness T2 of the vertical wings 118. On the upper surface of the third main wing 114, a pair of jet engines 115 are installed at left and right. The guide member 121 is installed toward the air inlet 115a of each jet engine 115 at the front portion of the upper vertical wing 118. Since the cross section of the guide member 121 is formed as an arcuate surface of the recess at the rear, the air inlet of the jet engine 115 effectively blows the air in front of the guide member 121 during the flight of the aircraft 110 of the aircraft 110. The efficiency of the jet engine 115 is improved by being guided and compressed to 115a. The angle θ formed by the guide member 121 and the imaginary surface 123 is selected in the range of 10-45 °, preferably 35 °, to effectively guide the air to the air inlet 115a. Since the exhaust port 115b of the jet engine 115 is installed to protrude rearward from the third main wing 114, the high temperature exhaust gas exhausted from the exhaust port 115b is blown by a part of the gas such as the vertical tail wing. To prevent them.

The first to third main wings 112-114, the vertical wings 116, 117, 119, and 120 and the upper vertical wings 118 made of a lightweight flexible material are hollow and pass through each other therein. Since the interior of the first to third main wings 112-114, the vertical wings 116, 117, 119, and 120 and the upper vertical wings 118 are filled with gas having a specific gravity lighter than air, the jet engine 115 This prevents the aircraft from falling even when it fails to gain momentum. The first to third main wings 112-114 are triangular to increase the sympathy in the main wing so that more gas can be filled. As the gas, rare gas such as helium gas and neon gas and natural gas can be used. In addition, the number of main wings is not limited to three, and a plurality of other main wings may be installed to increase the filling amount of the gas, and the body 111 may be filled with the gas. In addition, an internal combustion engine for driving the propeller and the propeller may be installed in place of the jet engine 115.

20 is a side view of another embodiment of the aircraft 150 of the present invention. The main wing 151 is disposed on the body 152 and the tail wing 154 and the vertical wing 153 is installed at the rear end of the body 152. The solar cell 156 is provided on the surface facing upward of the main blade 151. The lamps in the vehicle 150 are driven by the power of the solar cell 156. The solar cell 156 may be installed on a surface facing upward of the body 152 and the tail wing 154. In addition, the solar cell 156 may be installed to be disposed as shown by the phantom line 156 on the surface of the wing and the fuselage upwardly as shown in FIGS. 1 to 19.

The main wing 151 is made of a synthetic resin, a hard metal such as hard aluminum, etc., and is formed to have an inner space. A bag made of a flexible material is contained in the inner space, and the bag is filled with a gas having a specific gravity lighter than air.

The lower part of the main blade 151 is provided with a pair of jet engines 155 on the left and right.

Joint 158 is attached to the main wing 151, one end of the flexible tube 157 is detachably connected to the joint. The bags in flexible tube 157 and main wing 151 communicate with each other via joint 158. The other end of the flexible tube 157 is connected to a gas source 159 installed on the ground. The fuselage 152 is detachably connected to the ground via a plurality of wires (160). When the aircraft 150 takes off, the aircraft 150, which is filled with a gas lighter than air and is loaded with passengers and baggage, through the gas flexible tube 159 from the gas supplier in the air bag in the main wing 151, is mounted on the ground. It is no longer injured by the connected wire 160 and stops in a low injured state near the ground. In this state, the air sacs are filled with the gas until the vehicle 150 obtains the buoyancy of adjustment. After gas filling, the opening of the joint 157 is closed and the flexible tube 153 is removed from the joint 157.

Thereafter, the connection state of each wire 160 connected to the ground is released to allow the vehicle 150 to rise vertically on the ground. When the aircraft 150 rises to a predetermined altitude (about 100m), each jet engine 155 is started to allow the aircraft 150 to fly. During the flight, the lift is driven by the wing, so the aircraft can rise higher.

As described above, since the air vehicle 150 rises due to the buoyancy of the gas having a specific gravity lighter than air, the runway may be unnecessary or extremely short. In addition, the jet engine 155 may be started after being lifted from the ground to reduce the noise.

When the aircraft 150 lands, the gas filled in the air sacs in the main wing 151 is gradually exhausted through the joint 158 to reduce the buoyancy force on the vehicle 15. The joint 158 is bound to the aircraft of FIGS. 1 to 19 as indicated by the imaginary line, and is supplied with a gas having a specific gravity lighter than air through the flexible pipe 157 as in the aircraft 150, and then raised. Or start a jet engine to fly.

The bladder filled with gas having a specific gravity lighter than air may be installed in the body 152.

The present invention can be carried out in relation to a helicopter and the like can be used by filling the gas of a specific gravity lighter than air in the hollow rotor blades.

The invention may be embodied in other specific forms without departing from its spirit or main features. The above embodiments of the present invention should not be regarded as limiting the scope of the present invention represented by the appended specific claims, and many modifications and variations within the scope of the present invention should be recognized as belonging to the present invention.

Claims (3)

A fuselage 111 having an axis 122 in the flight direction; A first main wing 112 having a substantially triangular shape installed on the fuselage 111 in parallel to the axis 122 of the fuselage 111; At least one substantially triangular second and third main wings 113 and 114 installed at a distance (H1, H2) adjacent to the first main wing 112 above; The first main wing 112 and the upper second and third main wing (112), installed perpendicular to the axis of the fuselage perpendicular to the first main wing (112) and the upper second and third main wing (113, 114) A plurality of vertical wings 116, 117, 119, 120 interconnecting 113, 114; Solar cells 156 are installed on the upper surfaces of the upper third main wings 114 disposed on the uppermost portions of the plurality of upper second and third main wings 113 and 114 to supply power to the lamps in the vehicle 110. An upper vertical wing 118 having a vertical tail vane 125 on a rear surface thereof so as to extend parallel to an axis from the front portion of the upper third main blade 114 to the rear portion on an upper surface of the upper third main wing 114; The jet engine 115 installed in the upper third main wing 114 disposed at the top end and having an air inlet 115a in the flight direction and an exhaust port 115b protruding from the rear portion of the upper third main wing 114. ); And a guide member 121 extending from the front portion of the upper vertical wing 118 to the air inlet 115a of the jet engine 115 and guiding air to the air inlet 115a. The angle formed by the 121 and the upper vertical wings 118 is 10-45 °, and the first main wings 112, the upper second and third main wings 113 and 114, and the vertical wings 116, 117, 119 and 120 And the upper vertical wing 118 is made of a flexible material and filled with a gas having a specific gravity smaller than that of the air in the inner space. In the flying method of the aircraft 150 having a jet engine 115, a space filled with a gas of a specific gravity lighter than air inside the wing or the fuselage, in advance connected to the ground by a wire 160; Supplying a gas having a specific gravity smaller than that of air through the flexible pipe 157 from the ground to the main blade 151 from the source 159 until the air vehicle 150 floats; After completion of the charge release the connection of the ground and the vehicle 150 by the wire 160 to raise the aircraft 150 to a predetermined altitude almost vertically from the ground; And then starting the jet engine 155 to fly the aircraft 150. 3. The fuselage (111) according to claim 2, wherein the fuselage (111) having an axis (122) in the flight direction, and a flat first main blade (112) substantially triangular installed on the fuselage (111) parallel to the axis of the fuselage (111) One or more substantially triangular flat upper first main blades 112, first main blades 112, and upper and second upper and third main wings that are installed parallel to the first main blades 112 at equal intervals upwards A plurality of vertical wings installed vertically or parallel to the axis 122 of the fuselage and connecting the first main blade 112 and the upper first and second main wings 113 and 114 with each other ( 116, 117, 119, 120 and the upper main wings 113, 114 on the upper surface of the upper third main wings 114 disposed at the top of the plurality of upper second and third main wings 113, 114. The upper vertical blade 118 having the vertical cooking blade 124 at the rear portion so as to extend in parallel to the axis 112 from the front portion to the rear portion of the upper side; Jet engines installed at the 113 and 114, and the air inlet 115a faces the flight direction, and the exhaust port 115a protrudes from the rear part of the upper main wings 113 and 114, and the upper vertical wing 118. It includes a guide member extending from the front portion to the air inlet (115a) of the jet engine and guides the air to the air inlet (115a), main blade 112, the upper second and third main wings (113, 114) ), The vertical wings 116, 117, 119, and 120 and the upper vertical wings 118 are each made of a flexible material and have an inner space, and fill the inner space with a gas having a specific gravity smaller than that of air. Flight method of the vehicle, characterized in that.