WO2018186632A1

WO2018186632A1 - Flying device having rotating horizontal wings

Info

Publication number: WO2018186632A1
Application number: PCT/KR2018/003835
Authority: WO
Inventors: 이상철
Original assignee: 이상철
Priority date: 2017-04-03
Filing date: 2018-04-02
Publication date: 2018-10-11
Also published as: KR101873422B1

Abstract

A flying device of the present invention has one or more wings for performing a relative motion with respect to a body by means of a driving source so as to generate buoyancy, and has one or more air louvers provided at the wings and comprising openings formed at a wing frame, and slats provided in a part of a circumference of the opening so as to enable the opening to be opened and closed downwards according to air flow, wherein the body has two or more crank mechanisms, each crank mechanism has a horizontally extending crank shaft, and a crank pin moving in a circular motion while revolving around the crank shaft along a circle within a movement plane that is orthogonal to the crank shaft, at least one of the crank mechanisms is a driving crank mechanism for receiving the driving power of the driving source, two or more crank pins and two or more connecting parts of the wings are coupled so as to be rotatable in its place such that the wings are provided to become a horizontal position, and the wings are driven so as to perform a horizontal-position vertical circular motion, in which the wings move in a circular motion according to the crank pins revolutions while maintaining the horizontal position.

Description

Rotary horizontal wing aircraft

The present invention relates to a flying apparatus, and more particularly, the valve is closed in the opening during the lowering operation of the wing to maximize the air resistance of the wing, the valve of the opening is opened during the ascending action of the wing to reduce the air resistance of the wing One or more wings equipped with one or more gates perform horizontal circular motions (circular motions while maintaining horizontal) with respect to the body, enabling high-speed wing movements without overloading due to inertia resistance, and ensuring optimum phase and timing. The opening and closing operation of the buoyancy is maximized, to a manned or unmanned flying device.

In general, the fixed wing vehicle is lifted by the lifting force generated in the airfoil-shaped wing by the speed of the forward. And on a different principle, rotorcrafts (multi-copters, etc.) in which the rotation of the wing (propeller) with respect to the body creates a lift force is known.

In recent years, a flying device (see patent literature) that creates a lifting force by vertical lifting and lowering motion of the other end of a wing whose one end is fixed to a body (flying device body 8) by a hinge (wing shaft 34) is known. . This flying device is an air-gate wing flying device that flies by stirring the wings up and down like a bird's wing. Referring to claim 1, 'The air-gate wing flying device constitutes a wing that is thin, wide in width and short in front and back. It has an air gate (1) that is operated to be inserted into the shaft hole machined in the wing-like skeleton is formed to open and close like a door forward.

This flying device is configured to perform a motion that mimics a bird's wing. Thus, while one end of the wings (2, 3) is fixed to both wing shafts 34 arranged parallel to the longitudinal direction of the body (8), the wings (2, 3) are arranged so as to extend outwardly from the body (8) See drawing. In the blades 2 and 3, a crank shaft 22 fitted to the engine shaft 9 and a connecting rod 24 connected to the protrusion 35 attached to the blade generate relative motion with respect to the body 8 of the blade. Let's do it. The connecting rod 24 converts the revolution motion of the crank arm of the crank shaft 22 into a linear motion.

Therefore, the wings (2, 3), one end is invariant to the height of the wing shaft 34, the projection 35 is located on the opposite side of the other end relative to the wing shaft 34, the other end is connected to the connecting rod (24) By the connected projection 35, the circular arc movement around the wing shaft 34 is performed. In other words, the other end does not move at all in the front-rear direction of the body 8 during the circular motion. This, when viewed from the side of the flying device, is shown in the vertical reciprocating motion of the other end of the wing movement in the vertical direction.

As such, the other ends of the blades 2 and 3 are moved up and down by changing the direction of movement at the highest position (top dead center) by the connecting rod 24, and then descending by changing the direction of movement at the bottom position (bottom dead center). Repeat the operation.

[Preceding technical literature]

[Patent Documents]

(Patent Document 1) Utility Model Registration 20-0417261

However, in this prior art, there are difficulties in securing and commercializing sufficient flotation due to the following problems such as inertia resistance and instability of gate opening and closing caused by converting the rotational motion of the engine to the vertical reciprocation of the wing.

1) Engine overload and power loss are large due to inertia resistance due to reciprocating motion.

Due to the inertia resistance as the blade's direction of movement is suddenly turned 180 degrees at the top dead center and the bottom dead center, massive overload and energy loss occur periodically in the engine and connecting rod.

2) The larger the wing, the faster the movement of the wing.

When the width of the wing is doubled, the weight of the wing and the movement speed of the other end are doubled, and the inertia resistance is 8 times, so that the size of the wing and the speed of the wing motion are large.

3) The wing gate is not opened and closed in a timely manner, so the flotation generating efficiency is low.

Wings are linear movements, and the gate is a rotational movement, and then collide with each other, the gate opening and closing is irregular, and closes after falling more than the top dead center, low buoyancy generating efficiency.

4) Breaking sound and collision sound are generated at the moment of opening and closing of the gate, causing noise pollution.

Since the direction of movement of the wing is suddenly changed at the top dead center and the bottom dead center, at this time, the rotating gate due to the inertia force collides with the wing, and large pore sound and collision sound are generated.

5) The wings are heavy because thin, light and flexible materials cannot be used for the wings.

The thin and flexible material is bent or crumpled when the wing movement direction suddenly changes at the top dead center, and the gate opening and closing becomes irregular, so that the heavy rigid material is inevitably used.

6) Because the aircraft cannot maintain a constant altitude, it is difficult to use for aerial surveys.

As the wings of the wide wings fly up and down, the fuselage will also rise and fall accordingly, making it difficult to use for photography or aerial surveys that require maintaining a constant flight altitude.

7) Power transmission device that converts circular motion into reciprocating motion is complicated and heavy.

The power transmission device that converts the rotational movement of the power unit into a reciprocating motion is complicated and heavy, so that the frictional energy loss is large and hinders the support of the aircraft.

8) It is not possible to install a plurality of vanes having a phase difference on the top, bottom, left and right sides.

In order to make the load applied to the engine uniform and to maintain the flight altitude, it is necessary to install a plurality of wings having a phase difference on the top, bottom, left and right, but it is structurally impossible.

The present invention is to solve the problems of the prior art, it is to provide a technique that the rotational motion of the drive source is not converted to the vertical reciprocating motion of the blade, but is a horizontal circular motion of the blade as it is. because of this,

1) Eliminate overload and energy loss due to inertia force caused by reciprocating movement of the blade,

2) High speed wing movement without inertia resistance is possible even if the fuselage and wing are enlarged.

3) The wing gate should be opened and closed accurately and regularly at the top dead center and the bottom dead center.

4) It solves the vibration and noise pollution problems caused by the collision between wings and gate,

5) Thin, light and flexible material can greatly reduce the weight of the wing

6) Maintain the constant altitude without moving up and down according to the wing movement.

7) It is possible to install a plurality of wings having a phase angle of a certain angle up and down, left and right,

8) The aim is to provide a flight device that is very simple in structure, lightweight, durable and economically manufactured.

In addition, the wide and flat wing with horizontal circular motion not only maximizes the stability and flotation capability of the aircraft, but also provides the gliding function, resulting in higher market competitiveness and practicality than other conventional fixed-wing, rotary-wing or multicopter systems. It is to provide a simple flight.

The flying device of the present invention for achieving the above object has one or more wings for generating a flotation force by the relative movement with respect to the body by a drive source , the one or more gates provided on the wings, and the opening formed in the frame of the wing and In the flying device consisting of a valve provided in a part of the periphery of the opening to open and close the opening downward in accordance with the air flow, the body is provided with two or more crank mechanism , each of the crank mechanism is horizontal extending crankshaft and, along a circle in the movement plane perpendicular to the crankshaft and a crank pin to the circular motion with revolving about said crank axis, at least one of said crank mechanism includes a drive crank to receive transmission of the driving force of the driving source It is a mechanism , and two or more of the crank pin and two or more connecting portions of the blade can be rotated in place By being coupled to each other, the wing is installed to take a horizontal posture , the wing is characterized in that it is driven to perform a horizontal posture vertical circular motion in a circular motion according to the revolution of the crank pin, while maintaining the horizontal posture .

Here, the horizontal posture vertical circular motion of the wing is a repetitive circular motion which is repeated while the crank pin is circulated in the order of the rear end, the upper end, the front end, and the lower end of the circular trajectory, and the front end of the valve is the front end of the edge of the opening. It is coupled to a part of the side, by the acceleration force generated in the front end portion of the valve in accordance with the repetitive circulation motion tangential to the circular motion track, (1) at the upper end of the circular motion the valve is placed horizontally (2) from the upper end to the lower end, while the wing is closed by the valve, the wing descends and pushes the lower air to generate flotation force, and (3) at the lower end , the valve bends or swings about the front end of the valve. Like this, the door opens while rotating, and (4) the wing opens up from the lower end to the upper end, allowing the air above to pass. It is preferred that the lock be configured.

In addition, the crank mechanism is provided with three , the crank mechanism disposed in the middle , it is preferable that the drive crank mechanism coupled to the connection portion provided in the center of gravity of the wing.

The valve is preferably configured to be coupled to a part of the periphery of the opening rotatably as a hinged plate , or to be attached to a part of the perimeter of the opening as a light film made of a flexible material or an elastic material.

The vanes may be provided in plural in the front, rear, left, and right directions, and the plurality of vanes may be configured to have rotation phase differences of predetermined angles.

In addition, it is preferable that the steering mechanism for tilting the wing forward, backward, left, and right for further forward and backward direction change and progression.

According to the present invention, since the blades have a continuous horizontal circular motion, there is almost no periodic overload and power loss due to the inertia resistance, which is a fatal disadvantage of the vertical reciprocating motion, and is structurally simple and light, and the power transmission is efficient. Therefore, even if the wing size of the flying device increases, the wing movement at high speed can generate sufficient flotation force.

In addition, even if the wing moves at a high speed, the wing gate is completely closed at the top dead center where the wing moves in the horizontal direction, and the air is pushed down in the closed state until the wing moves from the top dead center to the bottom dead center. The flotation of the wing is maximized. On the other hand, by installing a plurality of wings having a phase difference of 180 degrees from each other, the problem of cyclic overload occurring at the time of falling of the blade is also solved, the energy efficiency is higher and the flight altitude of the aircraft can be kept constant.

In addition, since the rear end of the valve provided at one end of the gate is closed smoothly when the wing moves in the horizontal direction from the top dead center, the present invention provides a low noise, low vibration, high efficiency, low-cost flight device, personal flight, drone, etc. Can provide.

1 is a perspective view of one embodiment of the present invention having a power transmission mechanism directly driven by a drive source and having a pair of vanes provided on the outside of the body by a wheeled crank mechanism.

Fig. 2 is a (a) perspective view, (b) front view, and (c) side view of a configuration example in which a pair of wings is provided outside the body by a crank-type crank mechanism.

3A and 3B are diagrams showing the operation and configuration of the gate opening and closing.

4: (a) is a perspective view, (b) front view, (c) side view of the structural example which a wing is provided in two stages outward on the outer side of one floor, and the free end was carried out.

5A to 5C are a perspective view, a front view, and a side view of a configuration example in which wings are overlapped (bifold) on the outside of three layers (a configuration in which a plurality of wings are arranged at a first height and a second height different from the driving source).

6: A and 6B are a perspective view and a side view of the structural example with which a wing | blade was provided in the inside and the outer 1st floor.

7 is a perspective view of a configuration example provided with wings arranged side by side.

8A to 8D are a plan view, a front view, a side view, and an operation diagram showing a balance and steering state of a configuration example in which wide wings are provided on two layers.

9 is a perspective view of a train-like configuration in which a plurality of flight devices are connected back and forth.

10A to 10C are exemplary views of a square, curved, and streamlined wing frame.

11 is an exemplary view of a noise reduction gate.

Hereinafter, the present invention will be described in detail with reference to the accompanying drawings. However, the parts having the same function by the same configuration may be omitted because the same reference numerals are kept even if the drawings are different.

The flying device of the present invention is a flying device having one or more wings 40 which generate a flotation force by performing relative movement with respect to a body (body) 10 by the drive source 20 , as shown in FIG.

The body 10 is a member on which the drive source 20 and the vanes 40 are installed.

The drive source 20 is, for example, an engine or a motor, and imparts relative movement force of the blade 40 to the body 10. The drive source 20 can generate a rotational movement about the drive shaft d.

And as shown in FIG. 3B, the said wing | blade 40 is equipped with one or more base gates 44. As shown in FIG. The base 44 is composed of an opening 42 and a valve 43 provided for each opening.

The opening 42 is a vent formed in the frame 41 of the blade 40. The material, shape and size of the opening 42 are not particularly limited, provided that the valve 43 can be opened and closed in accordance with the lifting and lowering of the blade 40.

The valve 43 is a plate or film-shaped member provided around a part of the opening 42 so that the opening 42 can be opened and closed downward in accordance with the air flow.

The valve 43 is a hinged plate that is sized to cover the opening 42 and is coupled to a part of the periphery of the opening 42 so as to be rotatable like a swing door, or a light film made of a flexible material or an elastic material. (For example, thin and tough vinyl) is attached to a part of the periphery of the opening 42 so as to bend deformation.

The body 10 is provided with two or more crank mechanisms 30 . Each crank mechanism 30 includes a crank shaft 31 that extends horizontally and a crank pin that revolves around the crank shaft 31 along a circle in a movement plane orthogonal to the crank shaft 31. (32) is provided.

In the example of FIG. 1, two crank mechanisms 30 are provided, and the crank pins 32 provided at positions radially spaced apart from the crank shaft 31 (r) are provided with the crank shaft 31. It is configured to be an orbital movement around the center. The crank mechanism 30 may be formed of a crankshaft 31 and its periphery as a disc, and include a wheel type (FIG. 1) in which a crank pin 32 is provided on the disc, and the crankshaft 31 and the crank arm, And it may be comprised by the crank type (FIG. 2) which has the crank pin 32 at the front-end | tip of this crank arm, and these can add weight, such as a flywheel, to the point symmetrical position of the force point corresponding to a crank arm.

Two or more of the crank pin 32 and the two or more connecting portions 45 of the blade 40 are rotatably coupled in place , the blade 40 is installed to always take a horizontal position . Herein, 'rotating in place' means a coupling that is slipably installed by, for example, a bearing or a bushing. Since the interval between the installation intervals of the crankshaft 31 of the two or more crank mechanisms 30 and the two or more connection portions 45 of the blades 40 is invariant, the two or more crank pins 32 are synchronized in the same phase. Therefore, the said blade 40 becomes a horizontal posture in any phase.

And the wing 40 is driven to perform a horizontal posture vertical circular motion which is circularly circularly moved according to the revolution of the crank pin 32, while maintaining the horizontal posture . That is, as shown in FIG. 3A, while two or more crankpins 32 are circularly moved in a vertical circle about the crankshaft 31, the blade 40 is parallel to the line segment connecting the two crankpins 32. Maintain a horizontal position and do circular motions.

Here, at least one of the two or more crank mechanisms 30 is a drive crank mechanism driven by receiving the driving force of the drive source 20. The crank mechanism that is not driven by the driving force of the drive source 20 is a driven crank mechanism .

If necessary, a power transmission mechanism for transmitting the driving force of the drive source 20 to the drive crank mechanism may be interposed as shown in Figs. 5A to 5C. As the power transmission mechanism, for example, a friction belt, a belt, a gear, a chain, or the like may be used.

In FIG. 1, the front disc-shaped crank mechanism 30 is installed on the drive shaft d of the drive source 20, which receives the driving force of the drive source 20 and cranks the pin 32 around the crank shaft 31. It becomes a drive crank mechanism for idle movement. In addition, the crank pin 32 of the crank mechanism 30 in front of the crank pin 32 of the rear crank mechanism 30 can be slipped in phase with the two connecting portions 45 of one wing 40. Is connected. Therefore, as the crank pin 32 of the front crank mechanism 30 revolves, the crank pin 32 of the rear crank mechanism 30 also automatically synchronizes and revolves. The rear crank mechanism 30 thus becomes a driven crank mechanism.

However, unlike the example of FIG. 1, the driving force of the driving source 20 may be configured to be transmitted to the rear crank mechanism 30 through a power transmission mechanism, for example, a chain, a belt, a gear, a friction wheel, or the like. Thereby, the rear crank mechanism 30 can also be a drive crank mechanism similarly to the front crank mechanism 30. FIG. That is, the rotation synchronization and horizontal posture maintenance of the front and rear crank mechanism 30 may be made through the blade 40, but may also be made by a power transmission mechanism connecting the front and rear crank mechanism 30. .

Alternatively, a separate drive source 20 for generating a driving force for driving the rear crank mechanism 30 may be provided. In this case, a separate configuration for synchronization between the plurality of driving

sources

30 and 30 may be required.

Accordingly, the circular motion of the crank pin 32 of the front and rear crank mechanisms 30 (vertical orbital motion about the rotation axis r), the circular motion of the blade 40 while maintaining the horizontal (Horizontal posture vertical circular motion) . This is because the two crank pins 32 and the connecting portion 45 of the vanes 40 are slipably connected to each other.

As shown in Fig. 3A, when the drive source 20, for example, the engine or the motor, rotates, the drive crank mechanism 30 rotates, and the driven crank mechanism (30) is connected to the driven portion 43, the blade 40, and the other connected portion 43. Since the blade 30 rotates in the same phase, the blade 40 performs a circular motion (the crank pin 32 is an orbital motion) while maintaining a horizontal position. The horizontal posture vertical circular motion of the wing 40, as shown in Figure 3a, the crank pin 32 is circulated in the order of the rear end (right end), the top, the front end (left end), the bottom of the circular motion track a repeat repeated circular motions.

The front end (left end) of the valve 43 is coupled to a part of the front end (left end) of the edge of the opening 42. That is, the front end and the rear end in the operation of the crank pin 32 correspond to the front end and the rear end of the valve 43 and the opening 42.

Basically, the gate 44 is closed when the wing 40 descends according to the vertical component of the circular motion, and the gate 44 is open when the wing 40 is raised. Therefore, each of the gates 44 by the horizontal force and the vertical force generated by the horizontal posture and vertical circular motion of the wing 40 is closed during the lowering of the wing 40 to push the lower air down It generates a flotation force, and when the wing 40 is raised is opened to reduce the air resistance is operated in the direction to allow the wing 40 to rise smoothly.

However, the present invention is not limited thereto, and in the present invention, an acceleration force generated in the front end portion of the valve 43 in a tangential direction to the circular motion trajectory is generated according to the repetitive circulation motion. By this acceleration force, it acts to add a force in the closing direction when advancing the wing 40, and to add an force in the opening direction when advancing the wing 40. Specifically, the following four steps are repeated sequentially. In detail,

(1) At the upper end of the circular motion, the valve 44 is placed in the horizontal direction, and the gate 44 is closed.

(2) From the upper end to the lower end, the wing is lowered with the valve closed by the valve, and the air is pushed down to generate the flotation force.

(3) At the lower end , the valve opens while the valve is bent or rotated like a swing door about the front end of the valve.

(4) From the lower part to the upper part, the wing is raised with the gate open, allowing the upper air to pass through. The valve 43 changes from closed to open at the lower end, most open at the rear end, and changed from open to closed at the upper end.

The new wing of the prior art causes excessive force to enter a specific point such as a joint part (wing shaft 34), causing a failure, whereas the present invention, when the power of the drive source 20 operates the wing 40, Since the blade 40 moves in a circular position in a horizontal position, it does not take excessive force and there is little breakdown.

And if the wing simply flutters up and down as in the prior art, the energy loss due to the inertial force of the linear motion is large, the opening and closing of the gate is not smooth, the noise vibration occurs, and does not contribute to the effective lifting force. In the present invention, since the wing 40 is a horizontal posture vertical circular motion, the vertical motion of the circular motion, as well as the vertical motion of the circular motion as well as the forward and backward motion by the horizontal component of the circular motion, the rotational motion, the reciprocating motion conversion method By this, the merits of the rotational motion and the reciprocating motion are combined, so that the energy loss due to the inertia force of the linear motion is canceled by the forward and backward components of the circular motion, and the opening and closing are smooth. In addition, since the crank arm directly resists the tensile strength to the inertia force (centrifugal force) generated in the direction perpendicular to the crank rotational movement, the overload and power loss caused by the inertia force are basically eliminated.

In particular, in the prior art, when a thin, light and flexible material is used as a valve material of a wing gate, it is inevitably folded and wrinkled when the door is closed, but the rigid material has to be used. Since the gate is smoothly opened and closed with flow (the lighter and more flexible the valve, the less the influence of the centrifugal force due to the circular motion of the wing, and thus the closer to the tangential direction of the circular motion), the less the noise and vibration are generated. Also significantly reduces the weight, contributing to the effective lift.

Moreover, this invention is safer than a propeller. Since the new wing is applied, the width (distance between the left and right ends of the rotor blades) of the body is smaller than that of the rotor blades, and the rotor blades fall by hitting obstacles such as wires, or injury or property caused by the rotor blades. It is also less likely to cause phase damage.

Moreover, this invention is easy to manufacture. In the case of the conventional propeller type, two or three helicopters and four or more power sources are needed for drones. Therefore, output balance adjustment and centering are very difficult. In the case of the present invention, the power source (motor) can be configured with at least one.

The present invention can be applied to the wing of the bird, but can minimize the inertia resistance and weight of the wing, the shape and size of the wing can be fully enlarged, and can also be given a non-powered gliding function, in terms of energy efficiency to the propeller method It can secure a competitive edge.

Although the crank mechanism 30 is sufficient if it is two or more, it is preferable in particular if three crank mechanisms 30 are provided. In this case, the crank mechanism 30 disposed in the middle is preferably configured to be a drive crank mechanism coupled to the connecting portion 45 provided at the center of gravity of the wing 40. The crank mechanism 30 disposed at both ends serves to guide and balance the blade 40.

According to this configuration, since the driving force acts on the center of gravity, accurate operation is possible with minimal force.

The blades 40 are provided in plural numbers, for example, symmetrically in the front, rear, left, and right directions, and the plurality of wings 40 corresponding to the symmetry allow each other to cancel the noise and vibration caused by the operation, It is preferable to be configured to have a rotational phase difference of a predetermined angle so as to make the load uniform, to alternately push the air under the wing continuously, and to maintain the flight altitude and the high angle of the body constantly.

In other words, as the blades move downward, the load of air increases significantly, and when the blades move upward, the load of air decreases drastically, thus eliminating the problem of periodic overload applied to the driving source and the resulting energy loss. In order to maintain a stable flight altitude, high and low angles of the flying vehicle body, a plurality of wings 40 are arranged in symmetry, front-back symmetry, or vertical symmetry, and the periodic fluctuation of the rotation moment load that generates the flotation force is canceled. As a result, the flotation of the wing can be maintained stably.

The reason why the body body should periodically reduce the vibrations and shakes that rise and fall or tilt is that when the aircraft shakes during camera image, photogrammetry, or depth surveying, it cannot collect proper data.

For example, FIG. 4 shows an example of the offset configuration in the case where the phase difference between the first stage and the second stage blades 40 in the case of the two-stage blades 40 outward is 180 degrees.

5A to 5C show examples of offset configurations that reduce vibrations in the left and right directions and the up and down directions (phase difference 180?) By a pair of two-layer superposition blades 40 (biplane) structures.

6A and 6B show an example of the offset configuration when the phase difference is 180 ° in the case of the inner blade 40 and the pair of outer blades 40. 6A and 6B, the blade 40 of the center part of FIG. 6A and 6B does not have the blade 40 in front and back adjacent to the crank mechanism 30, and only the bar exists. This is because the portion corresponding to the rotation diameter of the crank mechanism 30 interferes with the crank mechanism 30. If only this part is removed, even if it is not made into the two-layer structure which uses a power transmission mechanism, the center blade 40 can be installed.

FIG. 7 shows an example of the offset configuration that reduces the lateral vibration by the pair of laterally arranged wings 40.

On the other hand, it is also possible to form one, two (180-degree), three (120-degree), and four (90-degree) arms of the crank mechanism. The shock and vibration that are applied to it are small and can move smoothly.

In this way, the wing 40 of the inner side and the outer side, or the left side and the right side, or the upper side and the lower side alternately pushes air down,

(1) The driving source 20 is not overwhelmed (resolves the problem of repetition of the air resistance generated and disappeared), and the energy efficiency is good.

② The eccentric load does not occur on the rotating shaft r (balanced force on both blades 40), so the vibration is small and the durability is increased.

③ Therefore, when the wing 40 rotates, the fluctuation caused by the change of the center of gravity does not occur, and it can perform a stable flight.

When the wing 40 is disposed on the outside of the body 10, the outer end of the wing 40 becomes a free end, so vibration may be generated. In order to solve this problem, a configuration for holding the free end of the wing 40 is preferable.

For example, FIG. 4 shows the structure of the paper | seat s in the case of the outer two-stage wing 40, and FIG. 5A-FIG. 5C show the example of the paper | seat s in the case of the outer upper and lower two-layer overlapping biplane wing 40. FIG. .

7 shows a configuration example having a pair of vanes 40 and a drive source 20 arranged toward the left and right sides with respect to the center. Since the front part of the valve 43 is on the outside, the wing 40 is operated outward when the wing 40 is on the upper side. Of course, if the front portion of the valve 43 is arranged in the opposite direction, the driving direction of the blade 40 is also reversed.

10A-10C is a structural example which used the frame f in order to avoid interference of the power source 20, the front and rear crank mechanism 30, and the blade | wing 40. FIG. By the frame f, the blade 40 can maintain a fixed distance from these power sources 20 and the crank mechanism 30.

The frame f may be manufactured in various shapes such as a trapezoid or a truss as well as the embodiments of FIGS. 10A to 10C, and combines the wings 40 having various shapes larger or smaller than the frame to the frame f. It is also possible.

On the other hand, when using the frame (f) as shown in Fig. 10a or 10b as the frame (f) of the blade 40 in the center portion of Figure 6a, corresponding to the rotation diameter of the crank mechanism 30 in the blade 40 Even if the part is not removed, interference with the crank mechanism 30 does not occur, and when the wing 40 is manufactured in a streamlined manner as shown in Fig. 10C, a gliding function can also be given.

Compared to the new wing of the prior art, in the case of the present invention, as shown in Figs. 8a to 8d, the size and shape of the wing 40 can be optimized according to the application, so that the horizontal posture vertical circular motion is It is possible. That is, the present invention, by adjusting the length of the wing 40 or the width of the wing 40, it is possible to optimize the lifting force required for the application field.

The wide wings of FIGS. 8A-8D only extend the frame 41 of one wing 40 forward and rearward, inward and outward of the front and rear crank mechanisms 30, and then only the front and rear crank mechanisms. Only the portion interfered with by (30) is left blank.

Although the shape of the wing 40 shown is planar rectangular, it is not limited to this, Any planar shape or curved shape may be sufficient.

Steering System

It is preferable that the steering mechanism 50 is further provided to tilt the blade 40 forward, backward, left, and right for forward and backward direction change and progression.

When implemented as a manned flight device, the cabin to be boarded by the user is provided below the wing 40 and the body 10, by enabling hardness in the front and rear and left and right directions, along with the role of weight, steering device 50 ) Can be easily installed.

When implemented as an unmanned aerial vehicle or a drone, by placing under the weight of the electronic device and the steering module body 10, such as a battery and a control module, it is possible to easily install the steering device 50 with the weight.

Steering

The drone method of arranging a large number of propellers is very difficult to adjust the rotational speed (floating force) balance between propellers, must be computer-dependent, very sensitive, and difficult to manually adjust.

On the contrary, for example, as shown in Figs. 8A to 8D, the steering operation of the present invention can be made to turn left (left turn) to the right (right turn) on the same principle as a hang glider. There is no risk of irregular left and right rotation. As the whole body 40 is inclined in the direction in which the wing 40 is tilted as the body moves back, forth, left and right, steering is intuitive and very convenient. When the user simply rides on a square footboard and rides one step forward, the wing 40 is tilted forward, and the aircraft moves forward, and when it is back, the aircraft goes backward, and when it moves to the right, the aircraft turns to the right. If you move to the left, the aircraft will turn to the left. Simply standing and moving only the center of gravity of the torso back and forth and left and right can lead the flight in that direction. In this way, for example, a single person can easily implement a flying vehicle. The rotation speed of the blade 40 can be adjusted by the handle like a motorcycle.

In the illustrated example, a person steers using a weight, but in the case of a drone, for example, a heavy object such as a battery, an electric field, a steering mechanism, etc. is disposed below, and the horizontal position is adjusted by an electric mechanism such as a piston or a ball screw. Can steer

As shown in Figure 9, by connecting a plurality of wings (40) and the power source 20 back and forth (cascade), it can be produced in a train type. If you make this shape long, you can fly like a snake. When the front wing 40 and the rear wing 40 are installed continuously, the crank pin 32 of one crank mechanism 30, the front and rear wings 40 are shared, and the wings 40 are raised and lowered at once. As you go, you can fly in a long shape, as if several people were rowing. In addition, by connecting a plurality of such cascade train type flight devices in the transverse direction, it is also possible to manufacture a wide and long flight device in which the unit flight devices are coupled longitudinally and horizontally. In this case, the unit flight devices disposed adjacent to the left and right sides are preferably manufactured to be connected to each other by connecting the crank mechanism 30 and the wings 40 to each other.

Therefore, the plurality of adjacent flying devices share a crank mechanism with each other, and may be configured to be combined with each other in the front-back direction and the left-right direction to increase the size.

8A to 8D, the wings 40 may be used to enable gliding like a bird. Having a gliding function can contribute to energy savings. As shown in Figure 10b, Figure 10c, if the inner side is concave like the wing of the plane, the upper side is convex to produce a streamlined, lifting force is improved, it is possible to further provide a gliding function. The material for gliding is not necessarily vinyl. The gliding will be affected by weight like a parachute, so adjust the curvature of the streamlined curve accordingly.

As shown in Fig. 11, for the quiet gate operation, when the gate 44 is closed, the front side (connection end) is brought into contact with the frame (opening edge) before the rear side (free end) of the valve 43, and smoothly. It can be closed without shock and noise. On the other hand, even when the valve 43 is formed to be significantly larger than the opening 42, when the gate closes quickly, the air layer that provides a cushioning function and does not completely escape air in the space between the valve and the frame or front and rear valves overlaps. As a result, the impact and noise are greatly reduced.

The example shown for this purpose shows the case where the opening 42 of the frame is curved downwardly convex and the valve 43 is planar. The valve 43 may be attached in a hinged manner, or may be an adhesive valve 43 made of a flexible material or an elastic material. When the wing 40 descends in this state, the valve 43 of the frame closes as the valve 43 bends upward due to air pressure. At this time, since the contact is gradually in contact with the frame, the problem that gives a shock and noise to the frame is suddenly closed while the valve 43 is closed. When the wing 40 is raised, the opening size of the opening 42 is also increased.

However, the present invention is not limited to the case where the opening 42 is curved and the valve 43 is flat. On the contrary, the case where the opening 42 is flat and the valve 43 is curved, or when the opening 42 and the valve 43 are both curved, belongs to the present invention.

When the lower vertical wall (side plate) is provided on the lower side of the wing 40, since the air in the partial lower space corresponding to the wing 40 area does not leak to the side but all pushes downward, the flotation force may be increased.

When the rear end of the valve 43 is slightly raised, the valve 43 does not turn over when reversing, and the valve 43 can be opened only when the wing 40 is raised.

The invention can also function as a fluid, for example a propulsion apparatus under water. The principle is the same as propulsion in air.

It is preferable to add a spring to the wing 40 of the present invention to double the lowering force. When there is no spring, when the wing 40 is pushed down to push the air, the load is increased, when the wing 40 is raised, the gate 44 is opened to reduce the air resistance, so the load is smaller.

Specifically, in order to compensate for this imbalance, a spring is provided between the lower end of the wing 40 and the body 10 under tension. The pulling force of the spring increases the winging force. When the wing 40 is raised, since the gate 44 is all open and rises without load resistance, the spring increases and serves to generate resistance (load).

As a result, when the wing 40 rises without an air resistance load, it additionally acts, thereby realizing an equal load upon rising and falling. That is, by adjusting the spring strength so that the load applied when the wing 40 rises and falls, the output power of the downward wing of the power unit is enhanced, the speed of rotation of the power unit is homogenized (load impact reduction) and energy efficiency. Pursuit of maximization (because it rotates at an even load).

Gate 44 arranged at an angle to the direction of travel (eg 45 degrees) can help to reduce shock and noise.

The opening 42 formed in the frame constituting the wing 40 and the remaining frame (opening opening) may be made of a wire mesh. By this wire mesh, the rise of the valve 43 is prevented, and the drop is allowed. In the form of the valve 43, if the front of the valve 43 to the wire mesh-shaped wing 40 (with a soft material, the head projection) can be easily removed and replaced when necessary.

Although the present invention has been described above with specific embodiments, the present invention is not limited thereto, and all modifications, improvements, and changes made within the scope of the claims should be interpreted as falling within the scope of the present invention.

The present invention can be used in the aircraft industry.

[Description of the code]

10: body

20: drive source

30: power transmission mechanism

40: wings

41: frame

42: opening

43: valve

44: Gate

50: steering mechanism

Claims

It has at least one wing that generates a flotation force by moving relative to the body by a drive source , the at least one gate is provided with an opening formed in the frame of the wing and the opening and closing downwards in accordance with the air flow , in the flight device composed of a valve provided in a portion of the opening perimeter so that,

The body is provided with two or more crank mechanism ,

Each of the crank mechanisms includes a crank shaft extending horizontally, and a crank pin moving in circular motion while revolving about the crank shaft along a circle in a movement plane orthogonal to the crank shaft.

At least one of the crank mechanism is a drive crank mechanism to receive the driving force of the drive source,

By combining two or more of the crank pin and two or more connecting portions of the blade to rotate in place , the blade is installed to take a horizontal position ,

The wing is driven to perform a horizontal posture vertical circular motion in circular motion according to the revolution of the crank pin while maintaining the horizontal posture .

Flight device characterized in that.
The method according to claim 1,

The horizontal posture vertical circular motion of the wing is a repetitive circular motion which is repeated while the crank pin is circulated in the order of the rear end, the upper end, the front end, and the lower end of the circular trajectory,

The front end of the valve is coupled to a part of the front end of the edge of the opening,

By the acceleration force generated in the front end portion of the valve in accordance with the repetitive circulation motion tangential to the circular motion track,

(1) At the upper end of the circular motion, the valve is placed horizontally, closing the gate,

(2) From the upper end to the lower end, the wing is lowered with the valve closed by the valve to push the air in the lower part to generate the flotation force,

(3) At the lower end , the door opens while the valve is bent or rotated like a swing door about the front end of the valve.

(4) From the lower end to the upper end is configured to pass the air in the upper portion as the wing rises with the gate open.

Flight device characterized in that.
The method according to claim 1 or 2,

The crank mechanism is provided with three ,

The crank mechanism disposed in the middle is composed of a drive crank mechanism coupled to the connection portion provided at the center of gravity of the wing

Flight device characterized in that.
The method according to claim 1 or 2,

The valve is configured to be coupled to a part of the periphery of the opening rotatably as a hinged plate , or to be attached to a part of the perimeter of the opening as a film made of a flexible material or an elastic material.

Flight device characterized in that.
The method according to claim 1 or 2,

The blade is provided in plurality , in the front and rear, left and right, or up and down direction,

The corresponding plurality of vanes are configured to have a rotational phase difference of a predetermined angle with each other.

Flight device characterized in that.
The method according to claim 1 or 2,

Steering mechanisms are further provided to tilt the blades forward, backward, left, and right to reverse direction and proceed.

Flight device characterized in that.
The method according to claim 1 or 2,

The plurality of adjacent flying devices share a crank mechanism with each other, and are coupled to the front and rear and left and right directions

Flight device characterized in that.