JP2008189032A - Flying boat and elevator - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a flying boat which can fly by running a short-distance from the water and land, glide and hover through the air at low speed, and gradually descend even if an engine stops. <P>SOLUTION: The flying boat 1 is composed of a main body 2 having a propeller 8, side wings 3, a side body 4, and a horizontal tail 5. In the flying boat 1, the horizontal tail 5 disposed at the rear part is formed in a reverse wing cross sectional shape where the tip end edge part on the lower surface is largely swollen than the upper surface of the horizontal center line L and composed so that the normal pressure is generated on the upper surface of the horizontal tail 5 and a negative air flow is generated on the lower surface during advancing. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a flying boat, and more particularly to a flying boat and an elevator that can fly over a short distance from water and can hover.

Conventionally, an airplane is configured in accordance with Bernoulli's theorem, and the center of gravity is set on the main wing. The longitudinal side surface of the main wing of the airplane has a so-called airfoil shape in which the lower surface is flat and set to a front-upward mounting angle, and the upper surface of the wing is bulged at the front edge. Naturally, the lower surface of the horizontal tail is not bulged.
By applying Bernoulli's theorem to this shape, the wind speed passing through the upper surface is faster than the wind speed passing through the lower surface of the wing during flight, resulting in a lower air density on the wing upper surface and negative pressure, Is said to be able to fly because it is lifted by the pressure difference.
However, in the above explanation, when the airplane is flipped over, the aircraft will sink downward, resulting in a contradiction in theory. In addition, if the aircraft tilts sideways during turning, the entire aircraft actually skids down diagonally, although it would normally rise upward.
As a result, the flight theory has recently been questioned and the flight theory has to be reviewed.
On the other hand, the main wing with a large aspect ratio whose width is longer than the longitudinal length is used for the wing, and those with a small aspect ratio are considered to be difficult to fly.
In addition, large and thick aircraft side parts and front parts have high air resistance during flight, making it difficult to fly. In addition, if the airplane is not flying at high speed, there is no lift on the wings, so it cannot hover.

Conventional airplanes require a long runway to increase speed when taking off and landing because of the main wing having a high aspect ratio.
An object of the present invention is to provide a flying boat that flies over a short distance from water and land, can perform low-speed glide and hover in the air, and can descend slowly even when the engine is stopped.

  The present invention does not have a main wing having a large aspect ratio, causes the wing to act on the entire lower surface of the fuselage, bulges the lower surface of the horizontal tail into an inverted wing shape, and allows high-speed airflow passing through the upper surface of the side wing to It is characterized by normal pressure on the upper surface of the wing and passing the airflow passing along the lower surface of the side wing at a negative pressure speed on the lower surface of the horizontal wing, allowing the flight to maintain horizontal stability by action before and after There is. The specific contents of the invention are as follows.

    (1) In a flying boat composed of a main fuselage, a side wing, a side fuselage, and a horizontal tail equipped with a propulsion device, the horizontal tail arranged at the rear is lower than the upper part of the horizontal core L on the longitudinal side surface. Is a flying craft that is formed in a reverse wing cross-sectional shape with a large bulging tip, and generates a normal pressure air flow on the upper surface of the horizontal tail and a negative pressure air flow on the lower surface during travel.

(2) The side wing is formed with a flared cross-sectional shape on the side surface, and the negative high-speed airflow passing through the top surface of the side wing is normal pressure on the top surface of the horizontal tail after passing the draft hole immediately after flight. The flight described in (1) 1 is configured such that the airflow passing along the lower surface of the side wing passes through the air vent hole and becomes negative pressure on the lower surface of the horizontal tail and passes backward at high speed. Boat.
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  (3) The horizontal fuselage L on each side of the main fuselage, side wing, side fuselage, and horizontal tail is set at the same level position, and is described in any one of (1) and (2) Flying boat.

  (4) The horizontal cores L on the side surfaces of the main fuselage, side wings, and side fuselage are set at the same level position, and the horizontal core L of the horizontal tail is slightly higher than that of the side fuselage. The flying boat described in any one of (1) and (2) above.

  (5) A secondary horizontal tail is disposed above the horizontal tail via a vertical tail, the top surface of the secondary horizontal tail is flat, and the bottom surface is swollen in a reverse blade cross section. The flying boat described in any one of) to (4).

  (6) The main body is formed in a substantially fish shape on a plane, the front part projects forward from the side wings, the upper part bulges larger than the horizontal core L on the side, and the lower surface is the lower surface of the side wings. The flying object according to any one of (1) to (5), which is set to be substantially the same.

  (7) The lower side of the side fuselage is greatly bulged downward from the horizontal core L, the rear lower part is formed to rise upward toward the horizontal core L, and the rear part protrudes longer rearward than the rear end of the side wing. Any one of the above (1) to (6), wherein a side tail that is aligned with the horizontal tail is disposed on the rear outer portion of each side fuselage with the horizontal core line L at the same level as the side fuselage. The flying boat described in.

  (8) The horizontal tail and the side tail, respectively, the upper surface is flat, and the lower surface is formed in a reverse blade cross-sectional shape with a leading edge bulging, according to any one of (1) to (7) Flying boat.

  (9) The flying boat according to (8), wherein the left and right side end portions of the sub horizontal tail are inclined upward or downward.

  (10) The propeller is a propeller type, and the propeller is disposed at the rear upper part of the main fuselage so that the propeller faces the air vent hole at the rear part of the side wing, as described in any one of (1) to (9). Flying boat.

  (11) The airframe is formed with a parachute storage portion having an opening / closing lid on the upper part, and the parachute is stored so that the parachute opens with airflow when the opening / closing lid is opened and thrown out in the air. The flying boat described in any one of (1) to (10).

  (12) An elevator used in an aircraft, wherein the vertical side surface is flat on the upper surface and the lower surface is formed in an inverted wing shape with the front edge bulging downward.

  The present invention has the following effects.

(1) The flying boat of the invention described in claim 1 is composed of a main fuselage, a side wing, a side fuselage, and a horizontal tail, and the horizontal tail is different from the horizontal tail of a conventional airplane and is above the horizontal core. Is flat, but the bottom side is swelled in a reverse wing cross-section so that the wing is reversed, so that it can be moved backward along the upper surface of the side wing at the front of the aircraft during flight. The airflow that passes under negative pressure escapes as normal pressure along the upper surface of the horizontal tail, the airflow that passes along the lower surface of the side wing becomes high speed on the bulging surface of the horizontal tail, and strong negative pressure is generated in the lower surface area. When the rear part of the fuselage is pulled down, the horizontal stability of the fuselage, which tends to fall forward, is maintained.
In other words, this flying boat is configured so that the nose is lowered and the reaction to the action produces the buoyancy of the fuselage while being pushed by the propulsion device. Therefore, in order to adjust the lowering of the nose of the horizontal tail, the lower surface of the horizontal tail is swollen larger than the upper surface as a mechanism for generating a negative pressure on the lower surface of the horizontal tail. Since the airflow flowing along the lower surface of the airframe passes upward at the end, turbulence does not occur.

(2) In the flying boat of the invention described in claim 2, the airflow passing at high speed on the upper surface of the side wing crosses the air vent at the rear end of the side wing, becomes normal pressure on the upper surface of the horizontal tail, and Break through. The airflow that passes along the lower surface of the side wing causes a high-speed airflow of negative pressure in the lower surface area of the horizontal tail wing beyond the air vents and exits backward, so the rear part of the flying boat is lowered and the nose is kept upward As a result, the airframe is stabilized horizontally, so that it is difficult for pitching to occur and a stable flight can be performed.
When the propulsion speed is slow and the velocity of the airflow flowing along the fuselage is slow, the velocity of the airflow passing along the upper surface of the side wing is slow, so that the lower atmospheric pressure airflow moves upward from the draft hole to a negative pressure. Supported by the updraft, the aircraft can hover.
When hovering, lift the nose and rotate the propeller, the airflow passing through the upper part of the side wing in front of the propeller becomes high speed and negative pressure, and at the rear of the propeller, the upper part of the horizontal tail is positive and the lower part Becomes negative pressure, and the force relationship works backward in the upper part and forward in the lower part, so that the aircraft can maintain a stationary state.
Also, when the engine stops in the air, the lower surface of the side wing surrounded by the left and right side fuselage and the air under the horizontal tail wings escape upward from the draft hole, so the aircraft descends slowly while rolling slightly can do.
In this case, when the airframe is light, the size of the air vent hole may be large, but when the airframe is heavy, it is preferable that the air vent hole is small in order to reduce the amount of air passing upward from the air vent hole.

(3) In the flying boat of the invention described in claim 3, since the horizontal core lines L of the main fuselage, side wing, side fuselage, and horizontal tail on the side are set at the same level position, the side wing However, it does not have a mounting angle and can be used at high speed during flight.
In addition, since the horizontal tail is at the same level as the rear end of the side wing, wind flow that passes backward at high speed along the upper surface of the side wing easily passes along the lower surface of the horizontal tail, and negative pressure is applied to the lower surface area of the horizontal tail. And push the tail down to keep the aircraft stable and level.

    (4) In the flying boat according to the invention described in claim 4, since the horizontal tail is arranged at a higher level than the side wing, the negative pressure airflow passing at high speed along the upper surface of the side wing is Higher speed airflow in the lower surface area and excellent maneuverability.

   (5) The flying boat according to the invention described in claim 5 is excellent in maneuverability because the auxiliary horizontal tail is disposed above the horizontal tail, so that rolling and pitching hardly occur.

  (6) The flying boat of the invention described in claim 6 has a Coanda effect on the main fuselage, does not cause turbulence in the air current, and has excellent levitation and advanceability.

(7) In the flying boat of the invention described in claim 7, since the side fuselage has a lower portion than the horizontal core L and bulges downward, the side fuselage can float on the water surface.
Since the front side of the side fuselage is large and thick, the Coanda effect is exhibited and the forward performance is enhanced. While the fuselage is moving forward, the side fuselage does not diffuse outwardly along the lower surface of the side wing, so the strip-shaped airflow is formed in a compartmented manner between the two sides of the fuselage below the side wing. As a result, the steering stability is increased without causing rolling or pitching of the aircraft.

  (8) In the flying boat of the invention described in claim 7, the nose is lowered because the lower surface of the side wing does not have an angle of attack with respect to the relative flow. The lower surface is formed into a wing cross-section with a large leading edge, so negative pressure is generated in the lower surface area of the tail during flight, and the direction of travel is raised with the nose going down as the aircraft moves forward To stabilize.

  (9) In the flying boat of the invention described in claim 9, since the left and right side end portions of the auxiliary horizontal tail are inclined upward or downward to form inclined portions, the straight boat is excellent in straightness and maneuverability. Are better.

  (10) In the flying boat of the invention described in claim 11, since the propeller type propulsion device is disposed at the rear upper part of the main fuselage so that the propeller faces the air vent hole at the rear part of the side wing, Since the airflow pressure passing along the lower surface is changed to flow rearward, even if the horizontal tail is at the same level as the side wing, it is excellent in stable maneuverability.

  (11) Since the flying boat of the invention described in claim 12 has a parasite mounted on the fuselage, when the engine stops in the air, it slowly descends, and when the parachute storage part is opened halfway, the parachute Will open and the aircraft will be able to land gently.

  (12) Since the elevator of the invention described in claim 12 has a flat upper surface and a lower surface that swells in an inverted wing shape on a horizontal side surface, when the rear end portion is raised upward, The wind flow that passes along it is negative pressure and passes at a high speed, so the elevator is pulled downward, so it has excellent maneuverability with the nose pointing up. When the elevator is turned downward, the lower surface bulges, so that the effect of lowering the direction is produced.

  A first embodiment of the present invention will be described.

1 is a plan view of the flying boat, FIG. 2 is a side view, FIG. 3 is a bottom view, FIG. 4 is a cross-sectional view taken along the line AA in FIG.
In the figure, in the flying boat 1, the main body 2 is set to have a fish shape like a tuna on both the plane and the side.

Side wings 3 that are long in the front and rear and have a narrow width are disposed in the rear half of the left and right sides of the main body 2. The lower surface of the main body 2 is set equal to or higher than the lower surface of the side wing 3. Reference numeral 1a denotes a cockpit.
Although the rear end portion of the main body 2 is shown at the same position as the rear end portion of the side wing 3 in FIG. 1, the main body 2 is short and the rear end portion can move to the front portion.

As shown in FIG. 4, the side wing 3 has a horizontal core L aligned with the main body 2 on the longitudinal side surface, and the vertical cross-sectional shape is set to a blade cross-sectional shape above the horizontal core L. The front part of the lower part of L bulges slightly downward.
As a result, the lower surface of the side wing 3 does not have a front-upward mounting angle unlike a conventional airplane. The side wing 3 is loaded with small luggage, fuel and the like.

A side fuselage 4 is disposed at the outer end of each side wing 3. The side body 4 is formed in a substantially tuna shape both on the plane and on the side surface.
In the plane, the front end portion of the side body 4 is rearward of the front end portion of the main body 2 and protrudes forward from the side wing 3, and the rear portion of the side body 4 protrudes longer rearward than the rear end portion of the side wing 3. .
On the side surface, the horizontal core L of the side body 4 is set at the same level as the horizontal core L of the main body 2.

  On the side of the side fuselage 4, the upper end of the upper side of the horizontal core L is set at the same level as the upper end of the side wing 3, and the lower side of the horizontal core L is a bulging portion closer to the front than the main fuselage. 2 is lower than the lower surface of 2, and the rear portion is set to rise.

An inner bottom portion of the side body 4 is set to a float, and an upper portion thereof is set to a guest room or a luggage room. As a result, as shown in FIG. 5, in the front view, the side fuselage 4 becomes a ship having buoyancy at the side fuselage 4 like a catamaran type ship.
This side fuselage 4 is excellent in running performance due to the stability and the Coanda effect even in water as a float of the main part of a boat.

Since both the main body 2 and the side body 4 have large front portions and are generally thick, some people think that the air resistance is large, the speed is not high, and they cannot fly.
However, since the main body 2 and the side body 4 are set in a substantially tuna shape, the Coanda effect acts greatly.

  That is, when a force is applied by the propulsion unit 8 from the rear to the front, the relative flow in the front part is compressed in the front part of the main body 2 and the side body 4 and the mucus is dripped back along the surface. It flows at high speed and no turbulence occurs. The main body 2 and the side body 4 are repelled forward with the passage of the relative flow at a high speed as a reaction of pushing the front part.

  This is because the pressurized air flow applied to the front part passes at a high speed so as to jump up when it is released from the top of the wooden piece floating in the water, and the pressure disappears. 4 jumps forward and moves forward continuously. Tuna can swim at high speed in the water due to the Coanda effect.

  A horizontal tail 5 is installed horizontally between the rear portions of the left and right side fuselages 4 at a position away from the rear end portion of the side wing 3 with the air vent hole 1b. As shown in FIG. 4, the horizontal core L of the vertical side surface of the horizontal tail 5 is set at the same level position as the horizontal core L of the main body 2. This is a feature that is different from the conventional airplane in which the phases of the main wing and the tail wing are made different vertically.

  As shown in FIG. 4, the vertical cross section of the horizontal tail 5 has a thin plate thickness above the horizontal core L and a flat upper surface, and the lower portion of the horizontal core L bulges like the wing upper surface. It is formed on a curved surface. That is, the airflow passing from the front to the rear along the horizontal tail 5 has a lower passage speed than the upper surface area, and generates a negative pressure in the lower surface area. This is also a feature that is greatly different from the setting of a conventional airplane.

An elevator 6 is disposed at the rear of the horizontal tail 5. In the plane, side tails 7 are arranged on the outer side of the side fuselage 4 along with the horizontal tails 5.
The side tail 7 is a substantially pentagonal plane with a front point, and is set so that the inside is long and protrudes forward, and is located forward of the position of the front end of the horizontal tail 5.

  The rear outer end portion of the side tail wing 7 is protruded to the outer side larger than the outer end portion of the side body 4. The horizontal core L of the side tail 7 is also set at the same level position as the horizontal core L of the main fuselage 2. The upper surface of the side tail 7 is flat and is combined with the upper surface of the horizontal tail 5, and the lower surface is set to have a thicker thickness at the front and inner portions, and is gradually set thinner toward the rear side.

A propulsion unit 8 is disposed at the upper rear portion of the main body 2. The propeller 8 is a propeller type with the propeller facing rearward and facing the air vent hole 1b. When this propeller uses a Version (trademark) type (Japanese Patent Application Nos. 2005-268828 and 2005-318126) with inclined wing tips, the wind noise is low and the propulsion is excellent.
Of course, the propulsion unit 8 may employ a jet type.

A vertical tail 10 is disposed at the center of the upper surface of the horizontal tail 5. A rudder 11 is disposed at the rear of the vertical tail 10.
In addition, the vertical tail 11 can be provided in a pair of left and right or three in parallel.

The flying boat 1 of the present invention configured as described above can advance as a boat by driving the propulsion unit 8 with the side body 4 floating on the water.
In this case, when the elevator 6 is turned upward, the nose is turned upward, and when the airflow passes rearward to the lower surface of the side wing 3 between the fuselage 4, the flying boat 1 as a whole rises, and the water contact area Can be reduced and propelled at high speed.

  Further, when the number of revolutions of the propulsion unit 8 is increased and the nose is directed upward, the surface effect on the lower surface of the aircraft is increased, and the aircraft can float above the water surface and glide. When gliding, the operation of the rudder 11 and the elevator 6 is the same as that of an airplane and can be freely controlled.

  The flow of the airflow when the flying boat 1 glides will be described with reference to the drawings. Above the horizontal core L, as shown in FIG. 1, the relative flow hitting the front of the main fuselage 2 is divided into the left and right of the main fuselage 2 so as to adhere to the surface of the main fuselage 2 at a high speed backward. It flows in. As a result, the relative flow is compressed at the front portion of the main body 2, and the airframe advances as a reaction in which the branched airflow passes backward at high speed.

That is, the Coanda effect is generated, and the airflow compressed in the surface area of the front end portion of the main body 2 flows backward at a high speed as the reaction, and thus passes as a negative pressure. As a result, since the rear part of the main body 2 is narrowed, normal pressure air from the outside surrounds the rear part of the main body 2 against a negative pressure air flow that is high in the front part and passes at a high speed backward. The main body 2 moves forward as a reaction.
Since the lower surface of the main fuselage 2 is substantially flat, the airflow passing backward is normal pressure, which pushes the fuselage upward.

  As for the side wing 3, an action in a normal wing occurs. The high-speed airflow passing through the upper surface of the side wing 3 passes through the air vent hole 1b, hits the rear horizontal tail 5 and changes to normal pressure along the upper surface. The airflow flowing along the lower surface of the side wing 3 flows at a high speed along the bulging surface under the horizontal tail 5 and becomes negative pressure.

  That is, as shown in FIG. 6, the relative flow hitting the front part of the side wing 3 generates a high pressure with a high air density at the tip of the side wing 3. The air flow branches up and down the side wings 3, and the air flow flowing along the upper surface becomes a high-speed air flow of negative pressure, passes through the upper surface of the horizontal tail 5 at the normal pressure at the air vent 1 b portion. . At this stage, the side wing 3 moves upward as it moves forward as a reaction that releases the pressure due to the high pressure at the front.

  The airflow passing rearward along the lower surface of the side wing 3 is prevented from diffusing laterally outward by the side fuselage 4 on the left and right sides, and is accurately guided rearward to the front of the horizontal tail 5. When it hits, it becomes high pressure and passes backward at high speed along the bulging lower surface, producing negative pressure. At this stage, the horizontal tail 5 descends as it advances. As a result, when the rear part is lowered from the center of gravity of the aircraft, the entire aircraft has a slight angle of attack with respect to the relative flow, and a stable lift is obtained.

On the other hand, the lower surface of the side body 4 has a Coanda effect similar to the main body 2, and the high-speed airflow passes rearward along each side surface.
That is, when the flying boat is gliding at 100 km / h, the negative pressure airflow passing at high speed along the lower side surface of the side fuselage 4 is faster than 100 km / h.

  Therefore, the airflow compressed in the front region of the side body 4 pressurizes the front part of the side body 4, branches along the peripheral surface, passes at high speed to the rear part, and becomes negative pressure. As described above, normal pressure air is drawn into the rear part of the side body 4 and the rear part of the side body 4 is pushed forward, and the side body 2 is pushed forward and advanced.

  Thus, this flying boat 1 causes a change in atmospheric pressure in each part due to the overall three-dimensional shape, and the change in atmospheric pressure pushes the entire body forward and lifts it up, Even if there is no such wing, the flying glide can be made safe.

  As described above, the high-speed airflow along the surface of the side body 4 passes between the side bodies 4 on the lower surface portion of the side wing 3. This means that an air current strip having a different atmospheric pressure from the surroundings is formed in the space. Then, as long as the flying boat 1 glides, the air current strip will glide like a rail, and is excellent in straightness. No. 4 acts as a balance weight of the heroine, and is less likely to cause rolling and pitching and has excellent steering stability.

  Due to the characteristic that the front of the main fuselage 2 and the side fuselage 4 are thick and large like a tuna fuselage, the center of gravity of the flying boat 1 is in the middle of the front and rear of the main fuselage 2, but the lower surface of the side wing 3 is in relative flow. On the other hand, since it does not have an attachment angle, when it glides, it tends to be in a forward-downward posture when pushed forward by the propulsive force of the propulsion device 8. The surface effect of the reaction raises the aircraft against the pressing action.

  On land, this flying boat 1 can take off with a short running distance of one third or less of a conventional airplane. This is because when the airflow is moved backward at a high speed by the propulsion device 8, the airframe is pushed forward by the Coanda effect as described above, and an upward lift is generated in the side wing 3. Raise the nose.

  Even when the propulsion unit 8 is operating and the forward flight is stopped at the time of gliding, as long as the airflow flows from the front to the rear along the upper and lower surfaces of the flying boat 1, the flying boat 1 has the elevator 6. With the above operation, the nose can be turned up and hovered at that position.

Even if the forward flight is stopped, the propulsion unit 8 is located above the side wing 3, so that the airflow generated by the propulsion unit 8 is faster on the upper surface than the lower surface of the fuselage. This means that the air pressure in the upper surface area is lower than the lower surface area of the fuselage, resulting in lift.
At the same time, the elevator 6 is raised and the nose is turned upward so that the lower surface of the side wing 3 has an angle of attack with respect to the relative flow, and the airflow passing backward becomes a wind against the lower surface of the fuselage. An effect is produced, and the descent of the aircraft is suppressed.

  When the elevator 6 is loosened to flatten the attitude of the airframe and the speed of the propulsion device 8 is reduced, the airframe can be lowered and landed gradually by weight. In this case, since there is an air vent hole 1b between the side wing 3 and the horizontal tail 5, the air can escape from the air vent hole 1b upward, so that the airframe is gently lowered on the spot without swinging. Can do.

  When the propulsion device 8 stops, it can descend almost in the same manner. As shown in FIG. 7, when the airframe does not have the air vent hole 1b, the gravity of the entire lower surface of the airframe is applied to the air, so when the airframe is tilted to one side, the lower repelling air escapes diagonally upward. Accelerate rapidly down the slope and crash.

  However, if the airframe has the air vent hole 1b, the air pressure in the air vent hole 1b does not generate the weight pressure of the airframe against the lower air. It flows upward from the portion of the hole 1b. The airflow that flows upward from the portion of the air vent hole 1b is one ascending airflow having a high air density, is linear, is restrained from lateral movement of the airframe, and if the air vent hole 1b is small, the airspeed of the airframe is lowered. Can be lowered slowly.

  For example, if you hold the paper horizontally with your hand and release it, the paper will sway and fall, and if you tilt it in one direction, it will drop suddenly, but if you make a hole in the center of the paper, it will keep the level while gently shaking. Descent. This is because the horizontal stability is maintained, only the hole part is not repelled by gravity, and even the air in the repelled part is diffused upward from the hole, so that the airflow rises through the hole from the surroundings. It is supported by an updraft like a pillar and can descend slowly without moving sideways.

  Note that the parachute can be stored in the airframe of the flying boat 1 by forming a parachute storage part (not shown) having an open / close lid on the upper part. In this case, the parachute can be configured to open when the opening / closing lid is opened and thrown out. Thus, if the parachute is opened during the descent, the impact can be landed gently.

At the time of gliding, the conventional airplane bulges outward and requires a large turning radius, and the aircraft slides sideways while tilting.
In this flying boat 1, even if the fuselage is tilted sideways, the left and right side fuselages 4 are positioned obliquely up and down. Does not occur. Further, due to the Coanda effect, a force that moves forward and upward of the fuselage works, and the maneuverability is excellent. Therefore, it is difficult to bulge outward during turning, and it is possible to turn with a short radius.

FIG. 8 is a front view showing the second embodiment. The same parts as those in the previous example are denoted by the same reference numerals and description thereof is omitted. In the second embodiment, vertical tails 10 are erected on the rear upper parts of the left and right side bodies 4, and a sub horizontal tail 12 is disposed at the upper end thereof.
The vertical cross-sectional shape of the sub horizontal tail 12 is the same as that of the horizontal tail 5. The sub horizontal tail 12 can be shifted to the position immediately above or behind the horizontal tail 5. Although not shown, a rudder is disposed at the rear of each vertical tail 10.

  In the second embodiment, since the vertical tail 10 is a pair of left and right, it is difficult to roll, and since the rudder is also a pair of left and right, the steering performance is improved. In addition, since the auxiliary horizontal tail 12 is disposed at a position higher than the side wing 3, biting is less likely to occur and the steering stability performance is improved.

  Inclined portions 12a that are inclined upward are formed on the left and right ends of the auxiliary horizontal tail 12, but this enhances the surface effect during turning and improves maneuverability, so it is excellent for rapid rise during short-distance running ing. The inclined portion 12a can be directed downward. Three vertical tails 10 can be arranged.

  FIG. 9 is a longitudinal side view of the elevator. As with the horizontal tail 5, the elevator 6 has a flat upper surface, but the lower surface is formed in an inverted airfoil shape with its front edge bulging downward. As a result, at the time of water smooth sky, high-speed wind similar to that of the horizontal tail 5 passes through the lower surface. When the elevator 6 is lifted, the upper surface is pressurized from the front, and the lower surface has a high speed air flow upward and negative pressure is generated. When the elevator 6 is lowered, the lower surface bulges, so that a rapid descent does not occur, so that the maneuvering becomes easy.

  The present invention is not limited to the above-described embodiment, and can be appropriately changed in design according to the purpose. In addition to the practical aircraft, it can be an unmanned radio controller. In that case, a solar power generation panel (not shown) can be attached to the upper surface of the machine body to provide a power source.

The flying boat 1 of the present invention can sprint freely on the water, and can also fly by short-distance sliding on land. It can hover in the air, land on land, and can be detached from the garden and ship deck.
Because of such high performance, disaster rescue, emergency rescue activities, traffic between remote islands, traffic on mountainous areas, traffic on plains and deserts, movement in vast ranches and premises, spraying of agricultural chemicals and fire extinguishing agents, complicated It can be used for land photography, fish detection with a fish detector, underwater terrain exploration with sonar, radio hazardous area photography, police and defense activities, fishing and other registrars, and other fields. .

1 is a plan view of a flying boat according to the present invention. It is a side view of the flying boat in FIG. It is a bottom view of the flying boat in the present invention. It is AA sectional drawing in FIG. It is a front view of the flying boat in FIG. It is a longitudinal side view of a side wing and a horizontal tail It is a vertical side view of a side wing and a horizontal tail during descending. 6 is a front view of a flying boat showing Example 2. FIG. It is a vertical side view of an elevator.

Explanation of symbols

1. Flying boat 1a. Pilot seat 1b. Ventilation hole Main fuselage Side wing 4. 4. Side fuselage Horizontal tail 6. Elevator 7 Lateral wing 7a. Aileron 8. Propeller 9. Propeller 10. Vertical tail 11. Rudder 12. Secondary horizontal tail 12a. Slope

Claims (12)

In a flying boat composed of a main fuselage, a side wing, a side fuselage, and a horizontal tail provided with a propulsion device, the horizontal tail disposed at the rear is a front edge on the vertical side surface, with the lower surface being higher than the upper portion of the horizontal core L A flying boat characterized in that it is formed in a cross section of an inverted wing with a large bulge, and is configured to generate a normal pressure on the upper surface of the horizontal tail and a negative pressure air flow on the lower surface during travel. The side wing is formed with a wing cross-sectional shape on the side surface, and during flight, the negative high-speed airflow passing through the top surface of the side wing becomes a normal pressure airflow on the top surface of the horizontal tail beyond the right draft hole, 2. The flight according to claim 1, wherein the airflow passing along the lower surface of the side wing is configured so as to pass backward at a high speed after passing through the draft hole, becoming negative pressure on the lower surface of the horizontal tail. Boat. The horizontal fuselage L on the side surfaces of the main fuselage, side wings, side fuselage, and horizontal tail is set at the same level position, according to any one of claims 1.2. Flying boat. The horizontal cores L on the side surfaces of the main fuselage, side wings, and side fuselage are set at the same level position, and the horizontal core L of the horizontal tail is set slightly higher than that of the side fuselage. The flying boat according to claim 1.2, wherein The sub horizontal tail is disposed above the horizontal tail via a vertical tail, the upper surface of the sub horizontal tail is flat, and the lower surface bulges in a reverse blade cross section. The flying boat described in any one of 1-4. The main body is formed in a substantially fish shape on a plane, the front part projects forward from the side wing, the upper part bulges larger than the horizontal core L on the side surface, and the lower surface is substantially the same as the lower surface of the side wing. It is set, The flying body according to any one of claims 1 to 5 characterized by things. The lower side of the side fuselage is greatly bulged downward from the horizontal core L, the rear lower part is formed ascending toward the horizontal core L, and the rear is projected rearward from the rear end of the side wing, The side tail that is aligned with the horizontal tail is disposed on the rear outer portion of each side fuselage, with the horizontal core L positioned at the same level as the side fuselage. The listed flying boat. The flying boat according to claim 7, wherein the side wing has a flat upper surface and a lower surface formed in a reverse wing cross-sectional shape with a leading edge bulging. 9. The flying boat according to claim 8, wherein the sub horizontal tail has an inclined portion in which left and right side end portions are inclined upward or downward. 10. The flight according to claim 1, wherein the propulsion device is a propeller type, and the propeller is disposed at an upper rear portion of the main fuselage so as to face an air vent hole at a rear portion of the side wing. Boat. The airframe has a parachute storage portion having an open / close lid on the top, and the parachute is stored therein so as to open when the open / close lid is opened and thrown out in the air. The flying boat described in any one of 1 to 10 above. An elevator for use in an airplane, characterized in that the longitudinal side surface has a flat upper surface and the lower surface is formed in an inverted wing shape with the front edge portion bulging downward.

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